NAVAi R Ol -4 0AVM-l

NATOPS FLIGHT MANUAL NAVY MODEL

A-4M A IRCRA FT

Douglas Aircraft Company, Long Beach, Calif. 90801 Controcl No . NOOOl9.70·C·0136

ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS ANO UNDER THE DIRECTION OF THE COMMANDER,

NAVAL AIR SYSTEMS COMMAND

FAl-2

l November 1971

I

NAVAlR 01 · 40AVM· l Section XI

SECTION XI

PERFORMANCE DATA

TABLE OF CONTENTS Pa rt

1nttoduction

GENEHAL • ••.... .. .

Per!ormance Data. Basis Abb1·eviations, Symbols, and Deflnitions ..... Drag Count lrldcx System . . . . Ai rspeed Corrections .. ........ . . Altimeter Corrections . . . .

TAKEOFF ....... . ... . .. • . . • .

Takeolf Charts . . .. ... . •. .. Operational Tnkeol! Di s tance ... •..• Maximum Tuke<>ll Weig ht - With and Without JATO .•.... JATO Firing Delay. Minimum Takeoff Distance - Two MK 7 MOD 2, 5KS-4500 JATO Bollles ..... . .... . Refusal Speed ... .•... . . . Stopping Distance .....• . .. • . . .. .

Page

11-1

11-3

11· 3

11-3 11-4 J 1-7 11-7

ll-7

11-7 11-7

11· 8

11- 19 11 · 20 11·20

CLIMB . . . . . • . . . . . . • . . • . 11· 31

Clirnb ... ............•...... Combat Celltog and Optimum Cruise Altitude

RANGE

Ra~e Facto r Chart . .. •. . • ... ... Fouled Deck Range ....... • .. • ..• Long Range Cruise • .. . . .. . .... .• Maximum Range Cruise ...... . . . . Nautical Miles per Pou1td of Fuel . .. .

INTRODUCTION

11-31

11-31

11-39

11· 39 11-39 11-39 11· 46 11 - 51

The operating data charls conlajned In this seetlon provide the p ilot with information enabling him to realize the ma.'<imum performance capabilities o! the ail'craft. Use o! the Ch:t.rt material for preflight planniflg and application o! the p1·e8c.dbed operating procedures wUl result in optimum eHeeth'<!ncss or the aircraft.

P ;trl Page

ENDURANCE ... .. . ..... •. . .. . . 11·63

Fouled Deck Endurance . . . . • . . . . . . 11-63 .Ma>:jmum Endurance 11·63

Alll HEFUELING . . . . . . . • . • • . . . . 11-71

Air Rcfuelifl!l Charts . . . . . . . . . . . . 11·71 Tanker Speed Envelope. . . . . . • • . . . 11 -71 T>nker Fuel Available for Tr~nsrer . . . . . . . . • . . • . 11-73 Tanker Fuel Transfer Time. . . . . . . . 11-73 Fuel Consumption of T;-mke r During Air Refueling • . . . . . . . . . . . 11- 76

7 DESCENT. • . . . . . . • . . • . • . . • • • . 11-79

Ma.'<irnuin Range Descent 11-79

LANDING • • . . . • . • • . . • . . • • . • . 11-83

Landing . . . . . . . . . • • . . . . . • . • . . 11-83

COMBAT PERFORMANCE . . • . • . . 11-93

Combat Perform:tnce .....• • . . • • . Turning Radius ..... . .... .. • • •. ManeuvetaMlity . . ....... .. . • .. M:\Ximum !\·Jach Number •••••.••.•

10 MISSION PLANNING • . .•. • . . ....

Mlsslon Planning . •• . •. . . . .. . •.•

11- 93 11-93 11·93 11-98

ll·lOl ~

11-101 'I Section XI is divided into 10 p;uts to present perrormance data in proper sequence for pl'e!light pl:tnning. Sample proble ms and charts arc pro­vided to present the sequence of steps required to !Ind the proper values and solution of" gi ven problem. Performance data are presented in ~ l:'aphiea l lyt>e charts for TCAO standard day conditions. In some instances . temperature corrccttons !or non·st:.indard atmosphere havo been Included.

ll· 1/(11· 2 blank)

NA VAIR 01·40AV~J - 1

PART 1

GENERAL

PERFORMANCE DAT A BASIS

Pt~rfor· m:\n('e data arc b:iscd on airc1·:'lft cha1-;u'l1;>n~· tics obtained Crom t\·4fo; f' N:l\'v and TA-1F Conu·ac ­tor flight tests. c:dcul:llions, and l'ngine dat:\ from Pr:1u and WhHnl'y speclftcalions. All chaJ'IS ~ire pre­scntC"d ro1· ICAO st:mdard atmo'31>hcrc conditions. althout~h ;:tmblcn· tcmperaturf• roJ·r pc·lion ~l·aLes a.re pr uv1dt*d in ot number of ch:1ris where 1em1><.'r::tture t'\ffc>Ns :1 r~· signlhcant. All P<'r!ormancc is bai=iPd on .\ centc1· of gr.1, ·1t\ poh1l1on of ?,.S percent MAC. All charts a rc 3Pl>lica.blc to J.P-4 or- ,JJ>-5 fue-l. havill(? a nominal <tensity of G 5 and 6. 8 J><>und~ per gallon r·espN' l "·ety.

ABBREVIATIONS, SYMBOLS, ANO DEFINITIONS

Ahhrf'\'iaCion

AOF

All

'C

CAS or V c

cc

do

Amb

eAS or v.

E(.;T

El'R

Dcfinihon

Tblio of SJ>eed of sound at ;iltltude Lo i;peed o{ sound . ll sea level. ICAO standard dav

Altt>rnat1ng C'\1rrent

Aoromalic direction findrng

Altitude

Calibr.1l~d .'lirs1>eed - (AS corre('tcd for position error

Center oi ~J'avi ty

Oil·e('t cu1·renl

Free s tream static condition

F.qtm•:tlenl airspeed CAS corrected for comprese>i w

blll!y e llec1

1-;xhaust gas temperature

J::nglnc prf.l-ssure r :1i i o

Abbreviation

F

Fii

FPi\1 or rpm

Ftcq

Fr or fl

g

Hor h

Ilg

hr

!AS or v i

!CAO

In

KCAS

Kl.,AS

KIAS

KTAS

Kts Kn

lb

M

MAX

min

min

Nl\l or Nl'\h

OAT

Scctio1) Xl Part J

D~finttion

Degr1>es F.thr<'nh~it

Flight

Ff'E>l per nunute-

Ft·<'qurnc~·

Ft> Pt

Gr.wlty forC't'

Alhtudp

1\h,:tC\ll'\'

Hour

hidic:Hed airspf'Pd instrunwnt 1·~1drng c.·or-TC('ted for instrumPnl error

TnlPrn:ihrJllal Ci\'il 1\\•iation Or~1111J:~tllon

Tnr:hcas

Knots calibrated airspt"("d

Knots equh13lcant airspeed

Knots indicated airSPtt>d

Knots tru~· airspcC"d

Knots

Poundi:;

:'\laC'h numl)("r

,\l,1ximum

Minul()$

Millimeters

Norrn:ll lood factor

NautiC'al l\lil!!S

Oi,1lside air temperature

11-3

Section XI Part I

Abbreviation

p

psl

RCR

RN!

RPM

SL

Std

T

TAS

Vol

Wt

6 or P/ P0

11·4

NAVAlR 01-40AVM-1

Dellnltlon

Static atmospheric pres w sure at any • ltltude

Static atmospheric pres w sure at sea level ICAO stand.ud day • 29. 92 Inches of mercuq •

Pounds per square inch

Runway condltion reading

Reynolds number index

Revolutions ~r minute (Engine speed)

Sea level

Standard

Static a bsolute tempera .. cure at any a ltitude

Static absolute tem1>era • ture at sea level JCAO stanc:t:ml d.1y = 288. 2 deg-rees Ke lvin

True alrspee<!

Volume

Weight

Oelta - <h<1nge in (e. g. gross weight)

Delta - r •tio o! sta tic alr pressur e to !CAO standa.i•d sea level static air p1·cssurc

Coemcient or rolling friction

Rho - density o( :Hmos­phere in slugs per root at any nltltudc

Rho - density or ahnos­phcre al sea level !CAO ol;rndard ct•y o. 002378 slugs per foot

Abbrcviatio11 Definition

Sigma - r atio o( density a t a ny altitude to density at sea level. tCAO Sh\nda r d day

Thet~a - r a tio of absolute UJ:rn1>en•ture of any alti­tude to absolute t e n1per a w

lure a t sea level; !CAO standar d day

DRAG COUNT INDEX SYSTEM

The la r ge variety o! external store lo"dings per· m1tted on the A · 4M a ircraft r equires a method or da ta pr esentation that can reflect a variable external configura tion. This method is called the Orag Count Index System.

Jn the Drag Count Index System. each item or the ex­cernal stor e configur ation. such as a bomb. tank. or pylon. is assigned a drag !'lumber· value lh::tl depends upon the slzc and shape o! the item and its location on the aircr aH. The sum o! these indlvldual drag number,!;. for 3 parti cular loading. reflects the dr3:g index for that conligur ation. This Index. when ;tp­

pUed lo the performance charts. de!ines the pe1·!or· mance of that configur~tion •

Some of the lndlvtdlU1 dr::tg numb()rJ:: us;()<! fo r deler ­mtntng drag tndexes arc shown in figure 11-1. and :i complete listing Is made In NAVAIR 01- 40AV · IT. Note th:1t lhc dr :tg m1 mbens (ot" ~' given store depend on thP store station on which they a re carried. The weights o! typical cxterm\l stort!S. pylons, tanks. and adapters are include<! in figure ll ·I, Tli. drag o! thl' C' l<'an aircra!t includes the dr ag of the centerline pylon. up1>er avionics pod. ln!light !ueling probe . and drag chute. bul no gums or wing pylons.

SAMPLE PROBLEM

Drag Indexes

(for figure 11 ·I)

Assume the external configur a tion consists of ::1 300w gallon Aero J WO ftiel tank on the centerline pylon . a Gx300·pound MK 81 Snakeye bomb clu•ter on each Inboard wing pylon. and a 530-pound MK 82 bomb on each outboor d wing pylon .

MODEL: A-41.1 ENGINE: J52-P-408

NAVAffi Ol-40AVll1-l

STORE DRAG INDEXES ANO GROS S WEIGHTS

DRAG INDEX FDR CLEAN CONFIGURATION <2l : O

STATION

STORES UP TO

50D(l)POUNDS STOR ES UP TO

IZOO(l)POUNDS

NOTE:

AIRCRAFT WEIGHT (POUNDS)

ESTIMATED WEIGHT EMPTY l:!J_ - -- - - 11,320 TWO 20 MM GUNS (NO AMMO)- - - - - - - 344 1WO AERO 20 A-1 RACK·PYLONS ON STATION 75 (2 AN04l-- - -- - ---- 140 TWO AERO 20 A-I RACK·PYLONS ON STATION113.75(! AND5l-- ------ 128 nvo 300· GALLON AERO-ID EXTERNAL RIEL TANKS (EMPTYl- -- - - 398 AAMORPLATE--- ---------- JOI

TOTAL OPERATING WEIGHT EMPTY-- - - IZ,437

(ll REFER TO NAVAIR Ol-4DAV·lT FOR CARRIAGE AND RELEASE LIMITATIONS, AND EXCEPTIONS FOR CARRIAGE OF CERT AJN STORES WEIG/I ING MORE TllAN Sl ATION LIMITATIONS SHOWN.

(21 CLEAN AIRCRAFT CONFIGURATION DOES NOT INCLUDE GU'-5 ANO WING PYLONS.

(3) OPERATING WEIGHT INCLU DES A CENTERLINE AERO 7 A -l

~g ~~~~1r~~l~8r6PJ~~J1:rf~fJNMJ~s~Ro'iftt~11UTE, ~Pcl\~f~~r~~¥J;, l\ND MISCELLANEOUS EQUIPMENT

Figure ll- 1. Drag Indexes (Sheet J)

Section XI Part 1

DATA AS OF: I DCCEMBER 1970 DATA BASIS: ESTIMATED

STATION

FAl-117

U-!l

I

Section Xl P:u·1 l

NAVAIR C!-401\V~l-l

Approx l)rag rndc•~ :ll Stort" Sr:nion

Gun~ and Su.i.p(•nsion I qufpmrnl \\'('htht

I 11)/ f'!l

l .... J_·-+---tiZ'

aoo HourliC.ls 20-mrn .\mmo 1-..~

Ont' A FHO 20A- l Jt:ld•-P\ lon 70

Onc> A I UC > :.'O,\ .. l lt:t<'k- f>'!;)Qn '" Al RO.;,.\-! l.aunche1· !m

A A J<R-1 MRR l.">9 II ,. II II

,, .\ 31n-:s v:umt ,7 ,, l' I'

TfR-1 !05 ,, 12 12

.\U,H-i 22:~ :!3 23 23

Approx Ot·~g Index n.t !)l..,tc 8-t::ition

T<t1\IU! ~lOO Pod~ (I) ;'\o. of W£>ight - --

Sl"SPf'l;~fOZ\' S1orcs Jblca 5

-I~ ···---J:>O-<OAr l-\1d Tank; A bHO ;.WA- 1, 7A-1 lJ50 1136 10 10

FC"U f"'.\IPT'l'1.! I

t 300-GA I. 1-\lel T:lnk At:n o 1A-1 22231 1'-3 15 fBol>t:iill: FU. I.

L.\IPTYf.?)

- ~

30<>-G:\ J. f\u:l T<lnk 1\ERO 20A-1 :n:i!.I ' l!m l·I ).I (4 F'in~l; rn.r F>IPT\'(,)

-----·U)(>-<,;AJ, f'Uel "f'!\nk: AlmO 'iA-1 2960/2·10 20 T'l' LL L.\IPT'l'fZ)

300-GA I.. Rt!luchng Afo~RO 7A-J 2765/725 30/ 11•!31 Storr; Fl' LL.I

EMPT\'(.!)

-c1·c--s:> Pod- A. Imo ZOA•l, 7A.-I J«-5/4~7 19 21 19 Mounlcd: Fl" LL/ EMPTY

i\<Yft;!): l. Hefcr to the l"iAVAIR Ol - 40AV- I T for :.ll other lJ)Ph<'abf(' <'Xl<'rmd store dr:i~ ind<'x :ind welghL d:-1~. c~1rna1te :u1d relC'ase U1n1tat1ons. and exct>1>tion" ror ('an-inge o f th(' bl0re$ w('ighing mon' th:in ~talion limilutaons noted on shf'.-L I .

2. fo\lcl tank wclghl for ,JP- 5 (uel.

3. Hos~ and drogue: retract.ed/ extC'ndOO.

Figu r e 11 - 1. Ong Indexes (Sheet 2)

11-6

NA VAUl 0 1-40AVM - I Section Xl Part l

Extel'1tal Drag Weight-Store Item Index Pounds

Clean aircraft

2 MK 12 20-mm guns 628 with 400 rounds ol ammuni tion

I 300-gallon Aero- I D 15 163 fuel tank on centerline

2 Inboard wing py:ons 12 140

2 o\ltboard wing p7lons 14 128

2 multiple ejector racks 46 446

R 2 5x300•pOund MK 81 70• 3000 Snakeye bombs

§

2 530-pound MK 82 6• 1060 bombs

Totals 170 5585

As the mission is flown, tanks may be d1·opped a1\d stores will be expended, changing the external stor e conJigu ration and thus the drag index.

•Reier to NAVAIP. 0J-40AV- JT.

AIRSPEED CORRECTIONS

Several correctto:ts to the airspeed indicator reading must be added to a r rive at the tr ue :lirspced of the :'lirc raft. Tu•o corrections peculiar to the indicator itself are instrument error and lag. These er rors , which are ue;ually small, a r e added a lgebraically lo the indicator readi ng to obtain the indicator airs~ed.

Calibrated airspeed ts equal to the airspeed tndlc.,tor r eading corr ected for position and instrument error. Po$Hion error , showo ln figure (to be Curnlshed at a tater dale) . ls an error intr oduced due to the loca ­tion or the s t.atlc source at :.. point of nona mbtent static pressure.

Equi va1cnl ai r speed is equa l to the airspeed ind.icalor r eading correct~ !or position error . Instrument er ror, and for thC' compressibili ty at a particular a ltitude.

True airspeed is r elated to equiva lent airspeed by the following: KTAS • KEAS x J/.[O

The quantity l //C may be found in figures 11 -3 and 11-5.

To conver t rallbrated airspeed to t r ue ainspeed and true Mach number .• figur e 11-2 is provided. fig-ure 11 -2 ha.s compressibility elfe:cts built into the graph permitting a direct step from calibrated to true airspeed.

A position er ror is assodatcd with the M:~ch number ind iCllted va lues :.nd the true Mrtch number va lues. TiliS relationship is shown in figure (to be furnished at a later date).

SAMPLE PROBLEM

Altitude Correction for Position Error

(For figure 11-6)

(Data lo be lurnisht'<I at a later date.)

Mach Number Correction for Po5ition Error

(For ligure 11 ·7)

(I>ata to be furnished at a later date. )

Airspeed Conversion

( For llgure 11·2)

(A) Calibrated airspeed 360 kn

(D) True pressure altitude .. . 25. 000 l l

(C) True Mach number ........... . . o. 849

(D) OAT. 2o·c

(E) True airspeed . 565 kn

ALTIMETER CORRECTIONS

The a ltimete r is connected to the ~tatic source. Pos it ion error. corrections, simibr to those for air .. speed Indications, must be applied to the a ltimeter lndlcattons to obtain t rue pressure altitude. The corrections :u·e given in figur e (to be rur oished at a tate r date). Instrument e r ror and altimeter lag ai·e ~lso prevalent In the a lthneter system. The lag error (approximately 200 leet) could be stgnlltcant in a low-a ltitude dive pu llout.

SAMPLE PROBLEM

Airspeed Correction for Position Error

(For figure J 1- 6)

(I>ata to be lurnlshed at a later date. )

11 -7

§

~

I

1.00

o.to

0.10

0.70

: • :E 0.60

~ % u

~ .., O.JO

~

0.40

O.JO

0.'20

ft.10

0 100

NAVAffi Ol-40AVM- l

AllSPllO CONVIHION

PlESSUlE ALTITIIDE-1000 FEET so so 20 10

700

-500

-100

EXAMPLE: 200

200

CAS : 360 KNOTS PRESSURE ALTITUDE= 25,000 FEET TRUE MACH NUMBn = 0.8'49 TRUE AIRSPEED !STD DAY!: 512 KNOTS TRUE AIRSPEED t20°C} = 565 KNOTS

soo 400 100 -CAUIRAtED AlltSPHD - KNOTS

Figure 11-2. Airspeed Conversion

... l5 z .. I

0 ... ... :l; .. :c ... :> .. ...

Section XJ Part 1

FA1·5~

11-9

Section X1 Part l

2.0

1.1 .io

00

... ill u. .,

b§ I~

Q I so

~ ... -.•os~

"' >- !:: t: !:; 'U ~41: ... >-

1.4 ,..... . .soc~

1.3

1.2

- .to

1.l t-:.ti: - 90

;±t

1.or-1.0

8 - 1.10

I •

~ 20 ... Q

NAVAffi 01- 40AVM-l

DINSITY ALTITUDE CHART

-•o -60 -4o -20 o 20 TEMPERATURE DEGREES CENTIGRADE TEMPERATURE DEGREES FAHRENHEIT

40 60

-1•0-120 -100-10 -40 -40 -20 20 40 60 •<> 100 120 140

.u .10 .1s .to .u .to .ts 1.00 1.os 1,10 1.1$

TEMPERATURE RATIO - 8

11-10 Figm·e 11-3. Density Altitude Chart

Dc-gn•cs Centittr:td~

-75 ·74 -73 -72 -7 1 -70 -69 -68 -67 · 66 -6f> -64 -63 -62 -e1 -60 -59 ·58 -57 ·56 -55 -5·1 -53 w52 -51 .. 50 -49 -48 -47 -46 45

-44 ·43 -42 -41 -40 -~9 -38 -37 -36 -35 -34

FAl-60

1\A VAIR 01 - 40AVM - I Sc.•<·tton X I Part 1

Dc>grt?(!S Jl\lgrl;!(l.S DegrCJ('S ~~,.e~s Oc-g1·t·t.•S. Fahrcnh~ll Centigrade f.,ht'f'nht'"H C~nlit:r-:\dt> F:ihrcnhclt

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I 47 llS. 6

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f igure 11 -4 . Ccntti:r ndc/ fahr cnhcli Conversion

11·1 1

SertlonXI Part J

Allllud<.• f<'et

St.ta l.t>Vf'J

1000

2000

3000

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0. 94SO

o. 93~1

o. 9312

0. 02·11

o. on;; o. 9100

o. 9037

O. S9G9

o. '1900

o. ;;s31

0. 8762

o. S09-I

o. "625

0. ~.:i5G

0»<87

o .•• ,, o. "f,3:j0

0 . h2M l

o. k212

fl.AH•

o. 807:>

O. ~OOG

o. 7:137

o. 7%9

0.17'\00

o. 7731

o. 71;02

I. 000

o. 9'11

0.99:1

o. 090

o. ooo

o. 983

o. ,79

O. 97U

o. 972

O.!MD

O. OGr.

o. 961

o. 950!

o. 954

(). 9:JI

o. 91'7

o. 943

o. 9-10

o. 9:JG

o. 932

o. 029

o. n; o. 92J

O. UJ'I

o. 911

0. q!,l i

o. ~ ... 7

o. C!~:J o. >79

o.n:;

2s.n1 2"l. '56

2i.r.:U

~6. 'SJ'i

24 . .. ~

23. 97S

:!!I. O"J.t

22.:2;2.j

21 31'."'

20. S71

U.79J

1~. 02n

Jit 292

17. G77

lh 'i1'(1,i

lti.2Hi

1$,.;jti~

"'· n12

14. 336

13. 7~0

13. l'"I

12. ;;:rn UL 1n7

J t 537

IJ. 104

10. b:.!1

JO. 10'1

9. 72!j

!'t 2~t7

I 0000 l),ltij.1..J

U.!t"l~'i

o. "~14;2 u. i,1;31

0. Q3i!O

O. ~01 1

l).i7h.\

o. 7420

u. 71•~

O. G>77

1J, 6r1M

0. 6360

0. bl13

Q. 5"175

0.5643

o. :;no l),j20!l

o. 499·1

0. 4791

() ... ;)!)~

O. ·l IOft

o. 1223

O.-I0-16

0.3.,:7G

o. J711

o. 35j2

o. :13~~ n. :t.!50

u. JJ07

o.n10 fJ,2<ii:l1

0.2709

I). 25"b

0.1·hl1

r.n IC.AO Stantfa rtl &-n Li•\·(•l .\tr lo t5 r

DATA BASIS: SAC.A T~C'hnf~l ~<ttC :->u. :U",::.?

J\0 2!1. 9i J tn. of II~ no Ml. · lnulS p0 O. 0<.12~7'i9 s lug IR'I' t'U fl

Figure 11-5. tCAO Stand.>rd Altitude Chart (Sheet 1) 11-12

Altitude f('('l

33. OO{J

36. 000

31), 0~!!)

3':' ,000

3'. 000

39, 000

IO. 000

.JI, OOQ

1.i. ono J3.000

11 . 000

-IS, (H.)0

·16. 000

1-: .noo I", 000

19. U(lO

so. 000

51, 000

.;2, 000

.;3, 000

54 . 000

s.;. ooo Sti,000

S?.000 .; ... , 000

,'i9.000

60, OOQ

Gl,OM

G2. 000

63,000

64. 000

G.5,000

Ht.o\1'\HKS:

lk"ll~ity Raho I

NAVAIR 01-40AVM-l

Tcmper:1tu1·c :ipf'<'<i of Sound H:itio

(f p " " ,fO (' •p Rntiu O T/l'

0 ;,1/ao

o. 3099

u. :W~ l

0. :?971

o. 2710

o. '!16:.!

O.:l:J.iG

o. 2236

o. 213J

0.2Q31

o. 1936

0. 1'-t.tG

(). 175"!

0. 1676

o. JS97

O. JS:?:!

O. U!\1

o. 13'3

o. 13J"

O. 1:?5G

0. 1197

o. 1111

n. 10~~ 0. 103t~

o. ()9'.<i77

Q, 09414

O.O;t!Ji2

o. o~;:i.:.1 o. 0~150 0. 07767

O. OH03

1.7!.164 - !'H.3·l2 - t;r •. 'tG

I. ~31ri - 56. 323 - 69. 3 .. 2

I. ~3 Ii -56. :100 -69. 700

l.!>209

I. 0077

~. OJS:.

2. 0045

2. 11'1"'

2 . 1662

2. 21-.:9

2. 27:.?~

2.32~1

2. 3..,4A

2. ·1'2Q

2. 5022

:?.5630

2.6~M

2. 1;~92

2. 7~·1G

'! . '216

2. ~903

2. !>GOG

3. O:t?G

3. 1063

3. J'-IJI)

3. 2503

3. 33RG

3. -U~"

3. :;029

3. si.;sa 3 . G154 -sr.. 500 .. G9. 700

(1) One in. of Hg 70. 73:.! lb p(>r gq !t 0. 4912 lb pCl' ~q Ill.

(), ;,;91

(), 752~

o. 7QJ9

o. 7.;t9

0 . '"':'1

O. "G';

(). 1-iG?

O. !o!G7

OAT;-\ RASIS: "ACA Tf'("hnlcal Sot<' ~n. 31~2

Pigur~ 11·5. ICAO Stand;1nl AltUude Ch;_u-1 (Shee' 2)

Section XI P;u·l I

In. u! fig Ratio 6 1>:p 0

i. 011

6. 7t2

.;.030

... 7!.14

-l.SG9

I. 355

·'- l.)I

3. 956

3. 710

3. 59:1

3 .. 125

3 :?t> t

3. IJ I

J. 9G.J

2. >12fo

,, :j67

0.23G3

(), :t~·~3 0.:.!;.?34

o. ~ 13"1

0.20:10:

o. HH2

O. l"';;I

o. l764

0.16"'1

0. 1602

\'), 1527

O. HSS

n_ l:l"17

u. lJ22

O. 121.lO

0. 1201

(I, I) 1S

O. lOfll

o. 1044)

0. O!l!)I

O. O!IM

o. onoo 0. OS~~

O. OHi~

o. 0779

0. ()7.1!1

;.! , Jl" 0.0709

2.0J°'i 0.01>1:;

I. !>24 o. 0043

L;>;3:J O. OGl:'l

1. 1·17 o. OS~1 o. 0$~7

11- 13

N'AVATR 01-40AVM-1 Section XI Part 2

PART 2

TAKEOFF

TAKEOFF CHARTS

The takeoff charts present takeoff distance. maximum takeoU we ight, JATO !iring delay, ond JATO ••keoU distance. The charts encompass such vari;tbles as takeoff weight, equivalent airspeed, ambient runway temperature, runway pressure altitude. headwind. ~nd runway gr-~tHt>ni H:ilf fl~ps anrl MILl'T'ARV thrust arc r ecommended for all takeo!fs.

Variables . which ar e not considered ln the charls, th.at will influence the acceleration of the a ircrafl during ground run a r e pilot bl':l.kin.g to mainta in di­rectional control; runwa.y surface conditions which constitute a Lower or higher value for the ro lling cocUiclent of fricUon (µ); extetnal store loadings on thE" wing stations which protrude forward or near the le~ding edge of the wing and influence the flow !ield of a.tr over the wing, reducing lift ::i.nd t ocreast ng re· quired takeoff Sl)eeds; and rough or bumpy runways which in.fluence the taxi attitude of the aircr;d'I, 1n· troduci1ig aerodynamic brak1ng during the ground run. Of these var iables, pilot bra.king, which is a function of pilot lechni~e, probably hos the gr~te•t !n!luence on acceleration· retardatlon and will incr ease the ground run sig?lificantly.

OPERATIONAL TAKEOFF DISTANCE

Oper<ttional takcoU distance, tolal di stance to clear a 50·foot obstacle, without JATO assist. <\nd rccom· mended takeoff speeds a r e show11 ill figu1·c ll ·8. Takeoff dist:1nces are based on h>lf ! laps. MlLITAIW

§ thrusl, and 8 <!egrees aircraft noseup t r im.

The t>keoH airspeeds and distances a r e based on NA TC flight test data o! the Model A-4E a lrcroJt . Nole the region in lhe altitude correction box wher e MA XlMUM TAKEOF F' WEIGHT MAY BE EXCEEDED. This region reprei;ents an area tn which the minimum 3ccept:1blc thrust·to·welght ratio may be encountered. resulting in marginal ciimbout capability, or tile safe tire limit speed of 175 knots ground speed may be ex· ceeded. Since temperature :ind a ttitude arc not in· dc1>cndcnt . the boun<bry lines tn this box a r e shown for extreme a ltitude ·tem1)e rature combinations. A moi;e detailed t1Xp lanation ot the margln:i.l rcglon is given undei:- m:1.x imu m takeoff wcit;ht . 'The method ol obtaining the ground run dlstance. total distance to clear a SO· foo: obstacle, take-Orf airspeed. and the llne speed cheok a1·e described In the following example.

Note

U operatiooal conditions require t;Lkeoffs for which comput ed takeof! distance places the o lreralt In the region l:1beled TAKEOFF IS l\<IARG!NAt. on the chill't. lilt-o!! speed should be increased approximatel~1 5 to 10 knots. not to exceed tire limiting speed. This wlll result in increased r;,ces of climb. Runway length ond loe:llion ol :ibort ge-u must be eons idered i n planning this type of takeoff.

SAMPLE PROBLEM

Takeoff Distance - Operational

(f'or figur e 11-8)

(A) Ta.keof! weight ..

(B) Tukeoll airspeed

(C) Ambient runwoy >Ir temperature . . .. . . .

(D) Run.way pressure a ltitude

(E) Headwind . .

(F) Runway gradient

(G) Gl'ound run di stance

(H) Total dist:in<·e to clear 50-loot obstacle

LINE SPEED CHECK

20. 000 lb

146 KIAS

3o•c

2000 ft

10 kn

·2 percent

2450 fl

3600 fl

A llne speed check is a s imple procedure for deter­mining that aircJ•a!t acceleration during takeoff run is normal. If alrcract acceleration is not normal, the line speed check 18 ~ufhciently early to allow normal braking to stop the ai rcr:afl on the runway. The pi lot selects a suitable and recognizatJle- known distance down tho runway from lhe poiut th~t t;'k '"o(( run commences (such as runway diSL~UtCt! m:1rkcr. runway intersection. etc.). The normal takeoff dis· tance ch;.\rt ls used by entering the cha.rt at the seler­ted disL:rnce and working in reverse throogh the ch:t.r t.

11-17

~ction XI Part 2

NA VA IR OI-40AVM-1

SAMPLE TAKEOFF DISTAN CE

-'--------~--:;,· '. --- . " ' ~ .

i N i

f4J·U'I

••pplym:.: thr c·orrectlons for \'aJ'i3tion from litandard coodttionl\. The fln;l lin,.. speed check .shuuld ht• m;idc nt the 2000·foot rut1\\':.t\· marker.

~ SAMPLE PROBLEM

I line Speed Check

(f'or hguri' ll-8}

(IO H~tlwmd

CM) AmhlPnt runw.l\' .dr· tc>n1pt-ratorc

(N) T .ikeo(! wt·iRht

(P) lndlc.Hed .ilrspecd

.. 2 ~rcent

10 kn

2000 It

30 c

20. 000 lb

t3:1 KlAS

MAXIMUM TAKEOFF WEIGHT - WITH AND WITHOUT JATO

The nlo.\Xin1um ink~off weight {Clgu tt..' 11 -9) is gt\'Cn :.s a fun<"tlon of pr(IS!-Our~· attitude .;ind ambient .air t('m· p~:rature- The d.11.1 ba.sts fo1· tins ch:.irl assumrs tl\.'\t tht' hntHng {!e:ir Es fully e:x-torwt<"d. takeo(( IA •ll ah-­speeds shown in figure 11 .. a. the aS rcraft is chmlJmg out w1111 ~TILJTARY th.rust w1lh lhP assist of gr ound cff('('I. multiplt> carrt3gc s tores ~u·e e1rrtt>d rm -A'ing

11-18

stations. nnd wing Claps :u·(' $Ct ~~l the 1l<llt-fl.1ps pos1tion. The m:tximum t.\k('<Jff wPl~hc '-'rtleria Is b~\scd on llu:i mm:n r r iltcttl or th~ followin~;

I. £xct'ls~ thrust Sh.'\ll not be less than mm1mum established b)' NA TC fligh1 •e•l

2. The safe t1re spee<l limit of 175 knots ~round SJ>C>cd ~ha II not l~ ex<.·e-edcd.

"\A 'TC rllght lest of the ~lodC'l A-4F. ai1Tr.1f\ shows that the abO\•e <'rit<"ri:l, when met. wtll pro"idc .u·· ccptnblc climbout ch.1.t:'lc·1~rislics. Since .JATO hurn­out 0t."cu1·s at lilt-oU. 1hi s ch:nt i~ \';thd for holh with :ind without JATO :isslst .

SAMPLE PROBLEM

Moximvm Takeoff Weight - Operational

(Por Ciri1Jre 11-9)

(A) Ambient runw;t)' air ccmpcr>ture. . . . 30 C

{B) Runw:w pr<:'SSore a ltitudc . . • . . . • . • . • . . . . . 1000 ft

(C) Maximum t:lkeo!C weight . . • . . 23. 220 lh

SAMPLE MAX IMUM TAKEOFF WEIG HT

llUUATUH - Oltl!US UlllUll(fT

I

NAVAIR 01·40A VM- l Section XI Pa.re 2

JATO FIRING DELAY, MINIMUM TAKEOFF DISTANCE - TWO MK 7 MOO 2, SKS-4500 JATO BOTTLES

The minimum &round run d(st.tnrfl ;1nd the total dts· lance to cl(>,ir ~ 50·foot obst.tclc m;w be re-Jlizf'd by 'lrl n{.! lh(.) .JATO boU !es 'JO th:u burnout occur s ill lfl·ofl. Burnout .1l hfl-orr Is recommended for the

fo llowan,I.( r·Pattans~

Burnout 3t llft·off produces the ,;hoJ·test tak{'-Qff dislal)CO.

2. A int.-;ure can be de>tC'-ctcd e.a r ly and the takeoff C...ln be :tllQrt('d v.•ell b~fore th~ refusal point.

ThP following 1rlm Settings are required for JATO 01>t!talion to :woid ext·cssh·c nosc .. htgh ;~tutudes ·'' low ~ross wei~hts du._. to noseup pltchln~ moments ~eneratcd by posslbl•• .JATO burning :l!ter li!l-oll.

Oro~s \Veigh' (Pound•l

13.500

17.500

22. 500

24. 500

ReC'ommcndc-d Tnm (0.1:Tees Noscup)

With 1he ;,bov"" reC"ommcnded trim settings. Hu.· flight trim Stick forct" \\ 1Lho ut ,JJ-\ TO burning \"O.J' les ll11P:1rly "'Ith e:r oss wct~ht Crum :1ppJ·oxhnatcl~· 12 pounds pull :u 16, 000 pounds ~ross weight to 3 pounds pull :tl 24. 500 poun<h;; JtrOS!; weight . 1'Ms Slick fore~ is not ob1cctton~1blc since .a redurtion In angle·o!-a.tmck is requ1rttd to maintain .1lrSJlflt>d o t· to <"Ontinu@ :tftt•lt•ratton

It ht rrrommen<led tt. .. 1t the fi r mJ.t lx.>int be est~blishcd bv c.tist:uw~ markct·s alongside the runw.1y. 1111s recommen<l1Hon 1~ 111ade for the fotlowtng r easons:

t. Vsinl! :\ tim<" inten~.tl from hr.lke r ele:tsc ls ''tm~iden:•d to he too lnncf"u?";Ht•.

2. l,;stng a irspeed as .t reference for ,JATO firing would not be posl'\lblt> sinl.'"e. gencrallv •• IATO U.ring occurs at a speed lwlt)w thfl speed 31 which U\C o\lr ~ spoed lndtc:uor begins to J'e~lsler.

Figure 11-1 O shows Lhe ground run di st:t.ncc Crom brake release to ignl!lon o! .IA TO. TakeoU speed. gr ound nm dist.\ncc. 01nd total horizontal dist:inre to

SAMPLE JATO FIRING DELAY

f'All41

r le:tr a 50-Coot obSl..lCIC arc presentc.-d In r1gur e t 1·11. T:'lkeorr distance" .i r e based on h:.1U-fl:q>s. ml1it~1rv ttu·ust. ornd trim st-thngs. ·

The L1keof( airspflrdK 3nd dtstances arc b:t~ed un JATO !light tesl d;i~1 CJ( tile ~lode! t\-11:; alrcr:t!t, ~ote 4he r ei,rion In tht .1ltitude corr ertton bo;'lt where ~IAXJMUM TAKF.on· \\EIGHT MAY BE EXCEEDF:n. This rl>glon 1«•prei;ents an :.tre:i tn which the ntlnimum :t<"CC))t:t.ble l hrusL-to-wcight l':lh<• may be enroun1ered. l'(•sulting In mar ginal cllmbout cap:ibihty. or th<" sale tire lhnillng SJlt!Pd al a?S knots ~round !=IJW~I m:'S be exceeded. Sinc-e t('mJJt'rah1re :\nd all\tud~ .1tt) not fndepPndent. the bound1rv Hn~s in this 1>0x a r<' shown for ext r t>me ;iltitudc-tcmpcJ'ature comb11-.;1hons. A mOl'e detailed E"XJ>l:lnarton of Lh~ r"U:\rgin,ll region ls gh·cu u.ndcr i\lnximum 'f3keoff Wcisrht. The melhod or obtaining the JATO !irin~ disla nre . • Jt\ TO takeoff ;u r~peed. JATO irroum.l run d1stanrP. and tot~tl dis- I lance- to clear :'I 50-foot obstu·t .. ls de"frihed ln the followin~ t':X:tmples.

SAMPLE PROBLEM

JATO Firing Delay

!For fig\lr e 11- JO)

l 1- 19

Section XJ Part 2

NA VAIR Ol · 40AVM • l

(A) Takeoll wetghl . .

(B) TakeoU airspeed . .

(C) A mbienl runway air temper:.ture . . .

{0) Runway pressure altitude ..•..•.

(E) Headwind ........ .

(F) Runway gradient

(G) JATO firing di•l:rnce

JATO Takeoff Distance

(For l!gurc 11-11)

(H) Takeo!! weight . . .......... (J) Takeoff airspeed

(K) Ambi ent runway a ir temperatu r e .

(L) Runway pressure alt itude ....

(M) Headwind .....

(N) Runway gradient

(P) Ground run d istance .

(Q) "rotal distance to clear 50-!ool obstacle .. .. • .. .. . .

Note

20. 000 lb

146 KIAS

30'C

2000 It

JO k n

-2 per cent

450 (t

20. 000 lb

146 KIAS

30'C

2000 ft

10 kn

-2 percent

1350 (l

2500 ll

Jettisoning of JATO bottles should be per­formed in 1. 0 g level flight. in cruise con­!iguralion. at 01" below 400 KlAS (maximum) .

REFUSAL SPEED

The maximum r efusal speed is that speed at which e l'1gine failure permits stop1>ing the airc•·a!t on a ru1\·

~ way or specl!icd lc11glh. figures 11· 12 and 11- 14 present this cb.t:i fo r engine faUure during a mlllt:iry thrust l.."1.keoH without JATO burning. Data i nclude$ distance coveJ·ea durlng a pilot reaction time ol 2 seconds and for an 8-sccond cnglne deceleration time B from mtllt>ry to Idle rpm. F igure ll·l2 IS without

• dr<lg chule deployed and figure 11-14 is with drag chute deployed.

11·20

SAMPLE JATO TAKEOFF DISTANCE

SAMPLE PROBLEM

Takeoff Refusal Speeds

(For Hgure 11-12)

Configuration: Al1 corl!igurations

(A) Runway temperature .•.. • ..• 3o•c

(B) Runway pressUJ'C ~ ltitude 2000 ft

(C) Tr:msler sca le ...... . 1.12

(0) Field len~th 8000 It

(P.) Takeoff weight . . 20. 000 lb

(F) Headwind . . . .. 10 kn

(G) Hunway t,rradient ....... . .. -z percent

(H) T:lkeo!! re!usal speed ...... . 91 K!AS

STOPPING DISTANCE

The slopping distance c harts (ligures 11-13 and 11-15) § a rc included primarily for use 1f the takeoff should be ~

NAVAm 01-40AVM· I S(>Cl1on XI Part 2

SAMPLE TAKEOFF REFUSAL SPEED

aborted. It ls not Ir.tended tor use In determlnirlf( l•ndin'( distance. The data does not Include pilot tcactton aud deceteralion tlme. Distances are based on the 3J>plication ol rna:<imum bra.king effort wilhout skidding the tires, tclow br:ikc energy limit speed, and throttle po15itioned at idle thrust. To minimlze dJvcrsion of pilot's ntention during this critical stage of the t3keoU abort, it is recommended Lh:-1.l fh1ps be

I lelt In the position selected for takcol!. F igure 11- 13 tj ls without drag chut• deployed, and figure 11-15 ls W with drru: chute doployed.

N ote

Slmttln~ down <he en1.'ine ~t 80 KJAS will shorten lhe J•olt•lUt considel"abh·.

SAMPL.E PROBLEM

Stopping Oistonce

(For figure 11-13)

Configuration: All Conf1gurahon~

(A) Runway tcmpcratw·c • • • • . • • 30' C

(D) nunw>y pressure o 1t11ucre . . • 2000 It

CC) lndlcaicd ~lrspced at abort . . . 91 KTAS

( D) Aircraft irross wct~ht • • • • • . • 20. 000 lb

(E) Heodwind . • . • • • • • • • • • • • 10 kn

( F) Runway gr~tdien1 . . . . . . . . . . -2 percenl

(G) Slopping dlstance . . . . . . . . . . 4500 rt

SAMPLE STOPPING DISTAN CE

t l-21

I

Section XI Part 2

170

160

ISO

140

130

120

110

0 ... ......... ~g~ s .,.,_§ :a-=: :~j 10

2

11-22

HALF FLAPS MODEL: A-4M ENGINE: JS2-P-408

0

NAVAl!l 01-40A VM-l

TAKEOFF DISTANCE OPERATIONAL 18° NOSEUP TRIM) NO JATO

DATA AS Of: I DECEMBER 1970 DATA BASIS: FLIGHT TEST (NAVY)

s 6

I I I I I 2 3 .. 5 4 7.

TOTAL DISTANCE TO CLEAR A SO FOOT OBSTACLE - I 000 FEET

Figure ll-8. Takeoff Distance

9

7

= :z: ..,z ..... ::>°' r- :z:

" " ..... ... .,. ...... ~ ... ..... r- ie

0

1

FA1- 14S-A

Q z ::> 0 ...

... £ "' < ....

HALF FLAPS

NAVAJR 01-40AVM- l

MAXIMUM TAKEOFF WEIGHT

Section XI Part 2

WITH AND WITHOUT JATO

MODEL: A-4M DATA AS OF1 1 DECEMBER 1970 ENGINE: JS2- P-408 DATA BASIS: FLIGHT TEST INAVYJ

25 ~ t: t:L.1 .. , •TAKEOFF WEIGHT LIMIT= 24,500 POQNDS r

t

24

23

22

21

::E 20 ::> ::E x < ::E

19

18 •NOTE:

17 . -20

WHEN USING C-11 /C .. 11-1 CATAPULT, MAXIMUM GROSS TAKEOFF WEIGHT IS 23,500 POUNDS.

-10 0 10 20

TEMPERATURE- DEGREES CENTIGRADE

I 0

I I I I I I I I I I 10 20 30 40 50 60 70 80

TEMPERATURE - UEGREES FAHRENHEIT

30

Figure 11- 9. Maximum Takeoff Weight

40 50

I 90 100 110 120

fAl-146-A

11-23

~

I

Section XI Part 2

11-24

NAVAIB Ol-40AVM-1

JATO FIRING DELAY

HALF FLAPS

MODEL: A-4M ENGINE: J52-P- 408

TWO JATO' UNITS

DATA AS OF: 1 DECEMBER 1970 DATA BASIS: FLIGHT TEST INAVYJ

170 ~~~~~·~,~~~~~~~~~~~!~. 160 ..._, "' -. ~. Q .• ~; ,., ...... ,

5

:i: 140 ... :); .. ~ 130

:i: =t 120 v i5 ~ 110

/ .,

t r

,.._.

JATO FIRING DELAY - 1000 FEET

Figure 11-10. JATO Firing Delay

FAl - 147-A

"' ... 0 z "' l fa ... ... "' "' < 0 ... < u i5 ~

170

160

ISO

140

130

120

NAVAill 01-40A VM-1

JATO TAKEOFF DISTANCE HALF FLAPS TWO JATO UNITS MODEL: A-4M DATA AS OF: 1 DECEMBER 1970 ENGINE: JS2-P-408 DATA BASIS< FLIGHT TEST lNAVYJ

Section XI Part 2

110 ,...._

-0 5 "TAKEOFF WEIGHT LIMIT = 20 ~ i : 24,500 POUNDS :> ~

TEMPERATURE llASEUNE: 4o :( :i

_ 60 ffi1.1.

NOTE:

= 80 ~ tn = 100 ~: -120 !e

0

JETTISONING OF JATO BOTTLES SHOULD BE PERFORMED IN 1.0g LEVEL FLIGHT IN CRUISE CON­FIGURATION, AT OR BELOW 400 KIAS (MAXIMUM!

s

FAl - 148

Figure 11-11. JATO Takeoff Distance 11- 25

I

Section XI Part 2

MODEL: A·4M ENGINE: JS2-P·408

WEIGHT BASELINE

NAVAIR 01-40AVM-1

TAKEOFF REFUSAL SPEED SPEEDBRAKES AND SPOILERS OPEN

HALF FLAPS NO DRAG CHUTE

DATA AS OF: 1 DECEMBER 1970 DATA BASIS: ESTIMATED

-20 -10 0 10 20 30 40

24 TEMPERATURE - DEGREES CENTIGRADE

22

20

18

0

GROSS WEIGHT - 1000 POUNDS

NOTE: BRAKE APPLICATION SPEED IS LIMITED BY SAFE TIRE SPEED. SAFE TIRE SPEED Will NOT BE EXCEEDED BY ANY TAKEOFF REFUSAL SPEED COMPUTED FROM THIS CHART.

20 HEADWIND

40

- KNOTS

RUNWAY GRADIENT - PERCENT SLOPE

so

so 60 70 80 90 100 110 120 130 140 150

REFUSAL SPEED - KIAS

FA1·149· A

Figure 11-12. Takeoff Refusal Speed - No Drag Chute 11- 26

NAVAIB Ol-40AVM-l

STOPPING DISTANCE SPEEDBRAKES AND SPOILERS OP~N

HALF FLAPS NO DRAG CHUTE

Section XI Pa1·t 2

MODEL: A· 4M ENGINE: JS2-P-408

DATA AS OF: 1 DECEMBER 1970 DATA BASIS: ESTIMATED

-20 - 10 0 10 20 30 40

TEMPERATURE - DEGREES CENTIGRADE

GROSS WEIGHT

- 1000 POUNDS

HEADWIND - KNOTS

RUNWAY GRADIENT

- PERCENT SLOPE

0

20

30

40

-2

4 6

STOPPING DISTANCE - 1000 FEET

Figure l l - 13 . Stopping Distance - No Drag Chute

10

FAl - 150. A

ll-27

I

Section XI Part 2

NAVAIB 01-40AVM-l

TAKEOFF REFUSAL SPEED SPEEDBRAKES AND SPOILERS OPEN

HALF FLAPS DRAG CHUTE DEPLOYED

MODEL: A-4M ENGINE: JS2- P-408

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

0

WEIGHT BASELINE -20 -10

.. I \~\\ \\\\\ ~ HEADWIND BASELINE

0

20

40

0

2 50 60 70 80 90 100 110 120 130 140 150 160

REFUSAL SPEED - KEAS

0 10 20 30 40 TEMPERATURE - DEGREE C

GROSS WEIGHT - 1000 POUNDS

HEADWIND - KNOTS

RUNWA Y GRADIENT - PERCENT SLOPE

fl

50

FA1 ·152

Figure 11-14. Takeoff Refusal Speed - With Drag Chute 11- 28

M O DEL: A-4M ENGINE: JS2- P-408

-20 -10 0 10 20 30

TEMPERATURE - °C

GROSS WEIGHT

NAVAIB 01-40AVM- l

STOPPING DISTANCE SPEEOBRAKES ANO SPOILERS OPEN

HALF FLAPS DRAG CHUTE DEPLOYED

40

24

22

Section XJ Part 2

DATE: 1S OCTOBER 1971 DATA BASIS: ESTIMATED

WEIGHT BASELINE

- 1000 POUNDS 20 ~ I I II ff// 18

0 HEADWIND BASELINE

10

HEADWIND 20

- KNOTS

30

40

- 2

RUNWAY 0 GRADIENT

2 0 4 6 8 10

GROUND ROLL DISTANCE - 1000 FEET

FAl - 153

Figure 11-15. Stopping Distance - With Drag Chute 11- 29/(11 - 30 blank)

I

NAVJ\11'1 01-40AVM-1 Scrtion XI P:H'l 3

PART 3

CLIMB

CLIMB

Climb ch•rts (figure• 11-16 lhrough 11-20) present Hu.• c•limh performanre for all drag index contigura­tions with the engi ne operating at milit.aa·y lhtusl. Cllmb speeds arc pl'cscntcd in Cigur•c 11· 16 as :1 func­lion of dr :.g index but independent or gross weight. The f·l imh 8peed st•hedule h:1 based on a minimu1n time to climb and does not repa·esent a n'l.;~ximum t·:.rngc cllmb.

J•ue-1. dtslanre. and lime to climb are presented in hgurtJ!i 11- l'l through 11-19 as a run('tion o f grou wf."1ght. prcssun: .dtilude. drag index. and tempera -ture deviation lrom ICAO stanctlrd day. The cb.ta ar c b:lscd on the climb speed schedule shown in fi~­urc 11 - 16.

SAMPLE PROBLEM

Climb Speed Schedule

(For lil(Ure ll-16)

(A) Crui~e :tltitude 30. OOQ fl

(13) Dr•g index . . . . . . . . . . . . . . . . . . 50

(C) Climb speed al Cl'uise (tllilud• . . . . . 292 KCAS

(D) Initial climb altitude • • . • • . • . . • . 5000 ft

(E) Climb speed at initial altitude ...... . 345 KCAS

SAMPLE PROBLEM

Climb Fuel

The method of presenting data for fuel. disl:tnce. and time is identic:1I; tho1·efor e, only one sample is shown.

(For figure l l -17)

(A)

( ll)

(C)

(0)

(E)

(F)

SAMPLE CLIMB SPEED SCHEDULE

' ' ' ' I I

' ' ' '

j

© : _________________ ....... ________ -l© ©i

lnilial gross weight . . . . . . . . . . . Cr uise allitude ... ..... . .. . .. Drag index ... . .

Temperature b.'\seline

·rempera lur e devialion from ICAO sland:u·d day ...•..... . • . .

Fuel to climb from sro level ................

FA,1•118

18. 000 lb

30. ooo rt

50

• lO'C

525 lb

COMBAT CEILING AND OPTIMUM CRUISE ALTITUDE

Combat celling. the altitude !or 500-lpm rate or climb with militar y lhnu;t, and optimum c ruise

11-31

I

Section XI Port 3

NAVA!R Oi -40AVM - l

SAMPLE CLIMB FUEL

altitude, the attitude that will produce the mo.xlmum cruise distance per pound of fuel, are presented in Ugure 11· 20. The data are presented ~'s a function of gross weight and drag lndex.

SAMPLE PROBLEM

Combat Ceiling and Optimum Cruise Altitude

(Por figure I 1-20)

J 1-32

SAMPLE CCMBAT CEILING AND OPTIMUM CRUISE ALTITUDE

FA1·120

(A) Aitcr:Ut gross weighl . . . . . . • . . . lR. 000 lb

(8) Drag index . . . • • . • • . • • . . . . • . . SO

(C) Comtx1t ceiling .......... . 40. 400 !t

(D) Optimum C'ruise altitude . . . . . . . . • 34, 000 ft

... E ~ w 0 :> ... ;:: ... ~

so

40

30

20

10

MODU: A-4M ENGINE: J52-P-408

NA VAIR 01- 40A VM- 1

CLIMB SPEED SCHEDULE MILITARY THRUST

DATA AS Of: 1 DltlMllR 1970 DATA BASIS: ESTIMATED

Section XI Parts

CALIBRATED AIRSPEED - KNOTS FAl - 121

Figure 11- 16. Climb Speed Schedule 11-33

I

Section XJ NAVA.IR Ol-40AVM-l NAVAffi Ol- 40AVM- l Section XI Part 3 l?art 3

MILITARY THRUST CLIMB MILITARY THRUST CLIMB MODEL: A·4M FUEL USED 1970 DISTANCE COVERED ENGINE: JS2-P-408

26 MODEL: A·4M DATA AS OF: 1 DECEMBER 1970 ... ENGINE: J52-P-408 DATA BASIS: ESTIMATED ...

26 ... 24

... ...

"' 0 24 0 ;? § z 22 :::> 5 0 "' "' l§ <t 0 ...

~ 22 § ... 20

.. 0 ~ :> ... "' ::: § .. "" 20 ...

% 18 C>

~ .. % 18 ~ < 16 ~ >=

~ ... 16 <(

14 >= ~

12 14

1400 12

1200 120

; i'

1000

< "' 0 g z 80 B :::>

800 <( a. z I I 0

:i! ... "' 600 :::> .. ... ... > ...

0 ~ u 40 400

STANDARD ... u

ALTITUDE TEMPERATURE z <( 1000 Fl. •c .. ~ 0 15.0 0

5 5.1 10 - 4.8

0 15 -14.7 IO 0 20 10 0 20 -24.6

25 - 34.5 /J. TEMPERATURE tJ. TEMPERATURE 30 -44.4

35 -54.3 -·c - •c 40 - 56.5

FAl-122 FAl-123

Figure 11- 17. Climb Fuel Figure 11-18. Climb Di stance 11-34

ll-35

Section XI Part 3

MODU: A · 4M ENGINE, J52-P-408

NAVAfil 01- 10AVM-l

MILITARY THRUST CLIMB TIME TO CLIMB

DATA A5 OF: 1 DECEM BER 1970 DATA BASIS' ESTIMATED

26 ~~---~~ ...... --~.·~~ ........

11- 36

"' 0 z :> 2 22

~ 20 t-!:ttff:~J~Ttj::l:ittffift !i: C!> w 3:

a 16 !

14

12

0 20 10 0

(j, TEMPERATURE -•c

ALTITUDE 1000 fl.

Figure ll- 19 . Climb Time

0 5 10 15 20 25 30 35 40

STANDARD TEMPERATURE

•c 15.0 5.1

- 4.8 -14.7 - 24.6 -34.5 -44.4 -54.3 -56.5

:;; ~

8 .. 0 :> ... ;:: ~ .. .. :>

"' ::: .. ...

:;; ~ 0

8

.. 0 :> ... 5 c( .. .. :>

E! .. ...

FAl-124

50

40

30

20

50

40

30

NAVAffi 01-40AVM- 1

COMBAT CEILING AND O PTIMUM CRUISE ALTITUDE ICAO STANDARD ATMOSPHERE

Section Xl Part 3

MODEL: A-4M DATA AS OF: 1 DECEMBER 1970 DATA BASIS, ESTIMATED ENGINE' JS2·P· 408

~

12 14 16 18 20 22 24 26

GROSS WEIGHT - 1000 POUNDS

14 16 18 20 22 24 26

GROSS WEIGHT - 1000 POUNDS

fAl-12_,

Figure 11- 20. Combat Ceiling and Optimum Cruise Altitude ll- 37/(11- 38 blank)

KAVAIR 01-40AVM-1 Section XI P:\rt.;

PART 4

RANGE RANGE FACTOR CHART

'rhe Range 1-"aclor chart (rib'\l r e l 1-2 l ) provldetJ a means or corretlh~ spe<'iftc {or tolal) ran~c tor cxi stln~ wlnct clfcets. The 1lrcs(!otcd range raccors constder wtnd speeds up to 120 knots Crom :tn}' rel:i­h\'e whu.-t direction for ;tire raft speeds or 350 to 500 KTAS.

USE

neterminc the reL1Uve wind direction by n1c:umring (jn a d<"K:kw1i;:e di re<;hon from tl1e Cui:scl:tge rcfo rcnrc plane) th<! angular dirh}rtmce heLWut.'n t he a irr rart hc:adlng 3n<l thc true wind direction. At 3 given wind direction. wind speed. and nircra.ft lrue :tir.i;pccd, read the r:111~c Cattor. Multl1>ly the ~pt:dfic ran~" by thls raf'tf{c factor :o obtaln sl)<'cUlc range as affected by wind.

FOULED DECK RANGE

I Occai;ions a rise duri 1~ carrie r 01>eralions whtm the deck bl'conu:~s fouled and nirctaft c:l.1\1\Qt be laken aboard until the <lzck Is c leared. In these Instances . 1t lb desir"bte for the pl10tl5 and the :ur o£Hcer to lte :tw~u·e o( t.hc range c-a1>:1l>ilit i<!8 of 1hc unrccovcr cd aircrnfl ·in tlrdcr ~hat an immediate decision t·:t11 be made concerning :he prope r cou rse or action. Should the Cblim:ued "clear deck"' lime be heyon<l lhe endur· anc(! time or the ain·raft, lhcn tho :ti r c r :lrt m\ISl OllhOr dep:lrl 1mrnE1d1ately for Lh~ bcneh u r land aboard the ready deck oC a..11othcr carrier, ii :'lVnil­ablc. However, If it Is c lthcr desirable or manda­tory that the alrcra!t orbit unill the deck ls c lea r . It is ncc<!ssa ry that the p11ot full y unde r stand the proper procedure to obtain t he maxim\lm endurance with the available fuel. Tile Fouled Deck Endui·ancc chart ts shown In !igurc ll -32 .

The routed OCc k Rongc cha1't (llgurc 11 - 22) tabula tes the range dist:1n<.:ts obtaln ... '\blc for ... arious quantllles of fuel on board at bnth the ini tial alHtuda and the optimum, best ranl<e altiludt:>. The aitcrnft coMigu· 1-ation consists of four empty wtng l»'lons plus guns, with o total dra g index or 33. Cllmb speeds and al r ­s1~~s fol' maximum range are included m the c h."}r-l as well as letdown tnstJ•uctlons.

The time at whi<"h letdown tS.hould l>e initiated iM gi\'e n in tCTf11s or fuel on board. and represents the fuel rcqutrcd to conduct :i ruaximum r ange descent from

altitude to sen level. A 250-pound !ut'l allnwan('f' l:ot tndudcd tor approad1 and bndinlt

Oinb'O llang:t :md Bmgo Range .. Oea r f>own chart:; are pr~~t'u1ed in fll:(UrP!' 11-23 :rnd 11-24 re~pec­Uvcly. These chnns arc 1.u•o,·idcd rot ao a.lrl"1~H configuration consisttni:c or four wtn.i: 1>Ylons. i:uns. ;rnd two 300·t..~llon f.'Xle r n:tl Cu~L t:tnks. with~ total dr:t~; 1 ud&,!x of 6 l wirh ~._.~, r up :lnc-! 391 with ~cnr down. The procedures Cor the ui-;.e of these <'harts nrc tden-1it':1I tn th02'e for 1he f-"'uul(•d l)(•rk llarn:t~ ('hart; how­~ver. an 800-pound fuel allow:rncc i:, included in mngo Range and mngo Ran~c - Gear Down charts !or approach ru1d londl111:.

LONG RANGE CRUISE

The Long Range Crut8C cha rts :t re 8hown m flgures-11 · 25 ll nd I 1 .. 26. Lang a'!l.11!-lC eruh~t· iSj defined n::; ihc hlghcsl Math number which will result ln 99 percent or the m:iximum miles 1>er J)O\lnd of luel. E'.sscntially. tong range cruiwe pcrmitsnn incrc:tse of 20 to 35 knots ln :iil'Sf><'f'd for an lncte:tsc oC I perccm in Cucl consuinptlon. To use the Lon¥ nange Cruts<" Ch:\tts . :werage gross weii;ht. drag index, ambient temperature. nnd de!;ircd rru1se a ltitude must be known ror a Jth'en cruise lei,:. With these k11own condhlons, 1011~ ran~c CJ'ulsc Mach nunlber. engtne power seutns ln lerms of EPIC and 6 pecHic r:l.ll!,rt! (naulu::.1 mile,. per 1><-Jttnd of fuel) can be determined. Th<! 01>tlmum long range cniisc altitudes arc aJso shown on flt-,rurc:.s lt-2a and ll -26. ~nd :l re the :altitudes th:u w111 produce- the maxtmum ntilet> per pound of fuel at the lon.: rnnge rruist> conditio11.

SAMPLE PROBLEM

long Range Cruise-Mach Number and EPR

(For r'b"'re 11 -25)

I ~, 000 lb

(B) Cl'\li$• :illitude. , , . 25. 000 II

11-39

I I I I I I l

I I I

I I

Scc·t1on Xl P>t't 4

11-40

Urlnth<' \\'Jnd-IJ('$:.ft·t"

I

K1 _\i;

t:'io

:)('l{l

:tao

:'!AVAii( 01-40,\V\1-1

"' IJ •. .,"lfj

n.:1r.11

i.n

o, "l.m

C),)o.jj(t

n.!'11 ll, "f\i

I). ~120 "· "i"" -0.9:.!i u. ">!il

'" 1110 l ..'O

n. ;1;:. u. ':11

0, · 0(1 n, jilt)

I.I. ;:1J

-- --1-----+-----11-----0. 'i.'*~ n. i..a:-.

0.'11'! v.-..i;:

I), ·~:i.. n. ~10. 'l. !! ii. (l.~11;

O,j1:J:l fl.fl:!':"

u,~t;','- O.:.i;JJ

n,nn-1 o.:.i~;.

C>.9!)ii (), 091

IJ.!IO'i 0.!":19:.!

n.!19':' O. ll!~ I

1.06:.! 1.01ti

l.Oi-4 1. n~:I

1,0li I. Oi:I

l.<>·•:t I . Uft'1

1.~:i"' 1. o'i:•

1.lfll 1.1.;:;:

J.Q...... l. l:JJ

1. 1)7~ l. Ui.

l. o;o 1.1'111

1.Ml 1.01111

1.111

J. 100

l.0'9

i.o .. o 1. l)~;t

(), .. jl

0. ~I~ j

o.~ ... o O.!f"'!..(

I),~!!;•\

l.1!'11

1. 11:.

l,l(ll

t.090

1. n .... 1

J.fj'o;

1.1~ ..

1. 112

I . l~!J

1 • • mo 1.lif::

1.1r.o I.HG

F'l~urc 11-21. Ra~o Factor Chart

l.l'ili

l.\lf;

L 130

1.11.-.

I. Jn~

1.:?:N

l. IV'I

I. JU:!

l.'.:'iC.

I . ~:to

t . :?;?2

I, 2110

l , JIO:!

0 . 0 .....

o. 'i;.!!t o. if;(I

o . .,.,~,

11.•u;I

o. •t':"J

1.211)

I.I";

1.lfM

1.11:!

I l t :

1.:n2 .. ~ .. , l. .? h')

l.J!J'.j

NAVAIR 01-40AVM - l

l>r:l):, JndC). • :Jj Afrer-.:.ft \\'i'tght tL"ss Fuel) • 12 ,030 l 'oundA

All J')'lone nod Guns ( ~o .\mmo) lh.:l!icn 't' fuel for J...:mUmg • :?:;O Pot.and&

Scctlo11XJ Part '1

Mo<h•l: A-·I M t:ng.inl•: JS~ -l'-·IOj

D:ttr> ."I~ nf: I J)c.rcmbu r rntO Ontn B:1H'w: fo .. J>l1m::l.h_·d

H You i\.l"f' nt Sen Ll'\'Cl

H:mgc .. Optimum A111tudc

:taoo :toG .iua 1900 167 393

r;oo J4i 34V

J :">00 l 27 291

1:100 lOT :l:t~

Optimum All nude

R:U!f[(' .. 10,000 Feet

If \•ou ·" '~ :it 10, 000 t'cct

H :Ulog(' .. Op1lmum Altitud.:

Opt1nmm Altitude

1t:.n1tt'

"' 20.000 Fc1..'l

If YQU ;\rt· :u :.!0.000 }c~t

tbnccc :d

Optimum Allitud4..•

Optin\um Altilud'-t

JU.000 290 /i ll:! 10.000 ;lu6 Saa 10.000

40,000 2M .Sl!I .I0,000 :l1.& l..&4 10.000

•o.ooo 200 ~&s ·~ .ooo 2~~ '02 .10,000 •10.000 1 ~2 31G ·10, oOO 2;;1 341 40,000 -.io.ooo l 55 :!6~ ·lO,ooo :?a us~ 10.000

r. JJ00 1-~·~"~-l-~~1~$~:._~~~10~.~oo~o__:-+__:1~2~·~r-~72~11,.-_,r~'o.:...o~o~o~-t---;177A:---t~~2~~s~-t:-4;;0:-.o:;;o;;;o_ ~-~ !iuo1-_:":::"-+-.:.'::3:l:__~•.:.o:.:·.:.oo:.:o__:-+-'-:o.;.o-f-_71:::j;,.--ir-'::'o:-' ::oo::o:--t--:'::,:-1 --r-:-,1~:;:'.,,.---i:-4;;0:-.o:;;o;;;o:-1 700 ,__:!_~~~-'0:_~1--.;."o:.:·::0070,.--t~~;::~~r-~-10::3:--~r-·::10:-. ::oo::o:--r~1::0':---t~:-·;;;--~-r~·~o:-.o~o~o:-soo JB ~7 15,000 4~ 5:1 25,000 07 73 30,000

! Hnn,::u

'" 30, oou J-'('('t

If You Ar, ~t ~o.ooo Fc.•(' t

H:Ulf:,C

"' Optimum Altitude

Optimum Ahitude

H:itlF[\' nt

~;. ooo J.'c4.'t

Ir \·nu Ar.- :u :lS,000 Fct't

Htmi.tc ., 0p(iMUnl Altitude

Optimum Altitude

na.ug\.' ., 40, 000

!"eel

lf Yt>U Arc :n +10,000 r- ... ,.t

H;J.ng<­ot

Optlmum Altllutle

~fmum .\U1tuch.•

2300~··~99::__--1~....:::j":.:·2__:--1___.:4:.:0.:.,o:.:o~o~-+--"~::",.--+-~-5~7~1~-t:-4::0~,0::0::0~-r-;'.5"::'9:--i-~-5~7::!'~-r--;'::O,~O~O~O­l901) i--:•:.:1:_0-1 _ _.:.·•r..::Mt___.:-1-•...:o.:.., o'-o-'o-+_'_s2_+--'-1_1_-t-',-,o_. 0:-:0.,..0_-t-:-1·::,9---t--4:-:':::9--t:-1::0~. o;;;o::o_ 11oni-:3~w=-~-1-~.:.•':.:1~~1-•:.:o.:.,o~o:.:o~-+-___.:•.:.•'=--1-~-'::':.:o~-t~'-:o.:...o:.:o::o~+--::'2::',.--t~~'::2::"~-t:-'::o~.o=o::o-1&00i-:a:.:".:.o~-l-~="1XJ~· __:~l-':.:o.:..oo:.:.:o~-+-_..:3.:.:;;i:__-l-~-3:.:G-:8~-t~4::0.:..,o::o::o~+--::"::'':--t~~3:;:'~'~-t--;'::o~,o=n::o-1:wo i1t 301 40.ooo 30:1 315 40.000 324 :•2·1 ·10.000

noo 1--...:2:.:2.:..•_-i...-1----=-·';;;_:_'.:.•:_-_-:,_-_.c.4~0.:...~oo~o~-=_-=_:-=_-=_~:.:·_&:i'"'·_-_-_-tt----_-_--:_2-s_2'=_-=_-=_~t=_-=_-.,.,1 0'=_.-::oo,__~,,o'=_-=_~t=_-=_~2~1.,..1::-----~:_-_-_-=2;1~-,_-_-_-~--~'::o~.-;;:o;;;o;;;::o~ oooi-.:t~s~2~-l-~=20=1__:~~·~0~.=oo~o~-+----=2.:.02:_-+~__.:.'~.:.J~-t~',-_".:..·",-_°",-:--1~~"~11:---t~-"~1::1~-t:-'=o~.o;;;o=o-100~1~3~5~+~~14~s:._~~~10~,=oo~o~-+-_..:1.:.so:_-+~__.:.1 s~1~-t~1~0~.o~oo~_,~71=~a:---t~--:-:'6~3~-t:-'::o~.o~o~o-500 :i,>i 91 il0,000 9M !l!l IOtOUO LO~ JIJ!o! lO. 000

~

Climb S.1](.'t.'tl Ocwcc.•nt Spi.-cd Start Ll•tdown Crom Alhtutlc.• Pn!tuaurc Altitmk! M11it:trv 11lru111l Cnnsc Spt•cd t.:ngtnt.• Idle - Sr.;1"':.o'C;::db:::rc:•::k<:_:•:_· l°'1c:.••°'c:.;:'d-t---''--'"'lh'-'-h'--""-'1 _1!,-,e_m_o_1n_1"~~·--

Full -Kc"s '~~. .._CAS l\t'1\ S l'ound~

G,000 10,000 13,000 :J6S

:!5,000 o. 783

30, 000 0. 78.1 o. 7fl.1

<0.000 0. 703 210 1"55

0.76;1 200 l SS

Fib"llr e 11-22. l'oulcd D•rk R•nge 11-4 1

Section XI Part 4

NAVA!ll 01-40AVM- l

Drag Index • GI Atr('rMt \\'eight (l.c&' 1-'u<'l) • 12 ,4a7 l'owkl$

All J')'lou~, Gun11. C No An1mo) , nnd 'T\\•o :JOO-Gallon 1-:x~rn:ll f~nkt< R(:ffCT\\I l"u.t.:I for L.andlng • AOO JJound11-

M1Jdul: A- -IM t;np.lnc: .J52-J''-10f.&

l>nl:t ns f'J'" 1 Dcc.·1.·m•.>cr 1370 Oatn JWutis· Ea;tlmatca

If \"ou Al'L' ul ~ti l.cvcl

ltnrig( 3t

OptJnmm Or,1fmmn Allllml.v AlUludc ,_ __ _,___ -

Rtlll'lp,4.' .. 10.000

FcN

If You Are al 10,1)00 Fflt1 t

R11nJ.li'-' al

O J1lm1uin l\ltiludt

fJµUmum A1tilude:

20, 000 J.'ccl

Jr Yoo Aro nt 20.oon •·~d

Run~c .. Ovt.huum Altiludc

0J)(imum AJtfU1d1•

NMf N"MI f4.'('l ~1'U ?\Ml Fl'(ll :-;'\u Nb.II n·<:t 1-~~+-~~~~1-~~~-+-- .---

2'0'00 171'1 100 40,000 25:.? '12.. 40.-000 --t-~3_4_1 -;---H_S_-t-~-0~,0-11<1_ 2500 lGJ 3DU 10, 000 :13? 36() .. o. 4)()0 :lOU 10•1 10, oan

2300 1 12 :iu .:o. ooo 202 ._ 3::.:3:.:&_4 _;•:.:0.:.;, o:.:o:.:.o_-1-...;.:!1.:.;s;_-+--a:.:5:.;;~_-+_'1-'-o~· '"'=-o

~~:: ~:~ ~:~ :::~;: ::~ -~,.-:;,.,:--+-,:c:~-::,.,:..,.:--1--,,.~o:-1 ::--+- ~:~ :~::: ·I- --+-----1-1---+---+-- --1----i 17001--"-"-+---t_'i:J __ t-_IO,l.>OO _ l20 10';' •t0, 000 17t 2:.!1 ..fO,llOO

, t.;)OO .;1 12;, .io, u_oo_-1-__ 10_0_+ __ 1_~0_,__,___10_._o_oo_-+ HO 174 -10.000

~ 13001-_4_8_-+-__ a_-J 30,000 1; -"f---'1-'-02'--ll-..;.·IO;.:•.;.o,;..OO;_+-''°'O..:.G_-\- 1211 10,~ t: 1100,__,_~-~--•1 __ 1s. ooo rn &s 2a,ooo ;2 'i9_~_3'-S-'-._uo_tt_

,§ UYou An.- 11l 30, 000 1'\:ct

If Vl)U At1..\ I'l l

a:;, ooo 1:cd U \ 'ou An• al 40,000 l"cm

----.-- --..----· - I ~

ll:iMg• 01

~o.ooo 1'\.•ct

r--­N''-U

2:Hl(I :J;Jfi r---

~100 :SU.i

190U 263 ..._ liOO 22J - -l&OU 1 7~ ,_____ 1200 1:ri' ,______ 110() 04

ftnnge .Kaq:i;l.l Hang-(> >t

011llmum AlUtut.lt:

n:tf16tl' ., ·10,000

F'ciPt

H:1n1u· ., Optlmu111 Allitllrk•

nr at Optimum 0Jl(lmum :i.i>, llUO Optimum

Allllufl*1 Optla1um

AltHUdl· Ahitudf' Allltudc• FeN

NMJ

IG1

1:?3

37.it

l'f'tt ~Ml :--'")U t~~d l\MI N'MI f.~t•N

·SU, 000 .i~G ----- -474 40, 000 ~ ~!l-+---l-'3--t--10_._0_01_1 _ ·Hl,O~ •l22 •l;il +-•;,;0•:.;;0.;;.00_;+-·-~~9-+--•..:.:J~'--f--'o,~,~~£._ 40,000 :n.... 31S6 40,0UO 3~S :rn:. IO,Oo('I_

.io,c>~I) ~\3a_-+--~-'-' --+-•-'o. ooo 3:'iO ~:to lO,ooo S0,000 26~ 2!.IJ 40, 000 :H'M &Ol lO,blJO

·•O,oou 24:t 2.itt 40, ooo :::67 :::-.1_-t_,_u_.o_o_o_ •l0,000 tM 2(12 1Q, UUU ;.!10 21U IU,O!ltl

-~

-ln. t>OO -+--1 :_,1_+ __ 1_r._• -+-•-o._o_oo_-t-_ 1G.l _ H-2 --+--'-"-· o_o_o _ rn.ooo HH au~ 40.000 11-1 11 ~ rn.ouo

'- ~ -~-~~~~~"'-~~~

Climb l>J.X'Ctl L>eFccnt Sflt't!<I Suui l..t't(k>wn frooi At&itudt .1'l'\IUU1"C Allltud1. MiHt1U'\' 1'hrulllt C'."nJitC' six·W t.n1ln~: hlh: - l"lpc"c."ffbr:t.k('J'i C10FCfl whh hu•I H1•nir_11_111_n~~--

l-0f't'I h('Af; M:ach No. h.(.'AS K C"A1= l'ounci~ -- ~~~~~~~~-1~~- ~~---

S·n5~~~~·l ~:~ ~~: _ ~ ~:~------+-----:~-~-----LO, 000 :1-40 2Gl1 -+------1-,7------t----..,:l~

I ~MIO ~IO._~~~--t-~_..:2~00:__~.+-~~~~--'1~~=7~~~~~-t----~~·~53.,;_~~~~-

20,001> !140 25$ 1 ~7 'l(j'j

--2-s-.-00-_o.~::::::::;::::_:--.,o-,. ,,..,r.4,.,..-- -t· z50 1 "l7 1.c1o10

30,000 Q.71H- 240 ,., ~9~ 3!J,U-O.):___-!----'o"-. ~7r,",4--t--~22:; 1~7 A01

10. 000 _ 1 _ O. 7&1 210 1S7 9H

-t!>1 ooo -~---o_. ·_.e_•-~ __ 2_0~~--~-----1~_1 ____ _ ....__ 927

11-42

~Hwl<'I. \· l~I En:.'1nt': J:>t l'-10~

2100

:nou ~aoo

2100

ln<lO

Jit10 ;fJ • foOO t 1:iuo I I IOO t l ! ~

~iUO

;?.'iOU

.:?!!Oo

!lOO

l:JOO

1700

1:100

1300

1100

Prrssure Ah nude

Fcu

Sfota L••\••I .i.000

10, 000

15. UtlO

ltJ,UOO

i:i . OOU

30.00<l

NAVAlR Ol-40AVM-I

lJl'tt:!lm.lL'll. 3!'1 t\1n·r:'IJ1 Wt'ii;::ht (IA''" Fod) 12. tii Jlouflc1"

:X,ctton XI Part -1

\fl P\lon,;0 Gun!> t~u \mmu), ;a:nd T\\O 300·<t:iJh>n L~1f'n1:il 1'!lJtkir. lh.•t.:('r\{ l\wl tor l_,;-mdm;t ..;oo roundl!

l( l w ,\re :u Sc:i LC\ c1

ltaJij.tl ;LL ll::ul.f:C :Jl lt:Ul~~ at Sc: a Opt1mun1 Upt1mum 10. uoo l.4.''t.'I !\)UU.i\l t.· ,\JtitUt.lc ~·c·1.·t

XMJ ~)U V~<'I :'\~II

1:.?t"I 2~6 30, 000 Uri

1(1 ... l'3 30. ooo ll"i

9:; J•JO ao.ooo t:JJ

,3 1:10 :10, 000 11~

10 113 30, 000 1•:• ;\'j >IU 30,0011 'l

I> r,$ .:.>.000 b~

:l:t 13 io. ooo 19

10 23 10, 000 33

It 'ou Arc at to. 000 l"ct:l

Rnng-1.1 al HtutJl.l :at l<am:c at :?O.UGO OpUm\ltn 011t1mum 30. U{)ll

t't•t.•I .\llJtudl• .\hllu1.h: Jl't.'l

:"\:\II KMI Ft't'l :\~U

;!J.'1 l3' 30.UtlO ~;;;,:

l~:-i 21:, 30 .000 2.~li >-

lil nt:? 30, 000 J(l(j

lG:i 16t1 30. ooo JS-2

1:u. JU 30,iJOO 1r .. ~ Ill 121 30. 000 l!J-1

M 91 !I0, 000 110

f"I 1:.! 30,0-00 l'l:'1

" I' l·l,,f)OQ lit)

Ol.:.!Ci.:nt Sl)('t-"Cl

Cllmb::i1"1CC'd Cruise t .. n:.tlnl' Hlk -

I( Yi.JU

IJ:tl3 :Lii of; J lkCcntlA.'J' l!/7\1 11:u:1 Baals: 1-.stun:ntd

\re at 10. 0llQ rc<'t

1-tan~l· al 0pumunt Of)tlmum 1\llitud4: ,\JtHmh.•

:ou FC~1

t:.!!l :10,000

:.!()() 30, 000

liG !JQ,tlUO

1 .. :~ :10. 090

I.?~, 30.000

Hl:'i :~o . ooo 'I 30, V\l'I .. 2.1.U1JO

3:; 2t.1,UOO

L( 'lw ,\n,: .l1 .:JO. UUO 1-t.·t.'I

IC:anu: :u llµUUmlll 0Jlht\1Um \1Utm1c.• \)UltH.lc;

i\MI lt:d

.!.;,! ;,H•.000

.'....!, ~U. OllO

2Uti JiJ,UUO

l"':l 30,000

n~ JO.Iii)\)

134 :so. UUQ

110 .to.000

,5 $0,ttu<I

li\t :so. uuo

--M .• 1-rt 1..<'ldo\\lt I" roll' .\llitodt:

M1Uu1.n· ·rhrusl !'JX-'(.'d b(-)Cl'dbrakctli (.'h.'1:;,t'<.1 Wllh rud IU.•m:ilnhll:

K(' i\S KCM.i l\C..: .\."'t Poundi.

;HO .! 1 ~ mo '"" 2•0 2JO JriQ '">) .J

:!·lO 2(1..; 1r.o ':w l IU :lU!i lli.O ·dtl --- ---l:iU "00 Jf.11 .. :;i)

.l(I:, l'J.) lbU 'i(,Q

l~.; J)'li!j 160 .. 10

figure 11~24. Bin~o Ra.nt.t(l Gear Down

tl-43

!

I

I ! I

Section XI Parl 4

3.4

3.2

3.0

2.8 0

~ .. 2.6 w .. :::> ;:a 2.• .. .. ~ 2.2

i5 ~ 2.0

"' 0 z :::>

~

... 0 .. Cl

~ .. ~

1.8

1.6

1.4

26

24

22

20

18

16

14

12

MODEL: A· 4M ENGINE: J52- P-408

NAVAIR Ol-40AV.M- l

LONG RANGE CRUISE MACH NUM BER AND EPR

DATA AS OF: 15 OCTOllEll 19 7 1 DATA BASIS: ESTIMATED

FAl - IU

Figure 11- 25. Long Range Cruise- Mach Number and EPR ll-44

"' 0 z :> 0 ... 0

8

..

26

24

22

x 20 I)

i 18 ::i 0 .. I)

~ "' ... > <

16

14

12

MODEL: A-4M ENGINE: JS'l-P-408

NAVAIB Ol - 40AV11'1-l

LONG RANGE CRUISE NAUTICAL MILES PER POUND OF FUEL

DATA AS OF: t 5 OCTOBER 1971 DATA BASIS: ESTIMATED

OPTIMUM LONG RANGE CRUISE ALTITUDE AT

DRAG INDEX 0 00

200

PRESSURE ALTITUDE

-1000 FT

0 s

10 15 20 25 30 35 40

SPECIFIC RANGE

Section Xl Pai·~ 4

ICAO STANDARD TEMP. - °C

15.0 S.1

-4.8 -H.7 -24.6 -34.S - 44.4 -54.3 -56.S

- NAUTICAL MILES PER POUND OF FUEL .05 ,1 0 • • ~ .20 .25 .30 .35 .40

t

FA1· 167

Figure 11-26. Long Range Cruise-Nautical Miles per Pound of Fuel

11-45

!';ection XI Part 4

NAVAIR 01·40AVM- I

(C) Orll{I: index JOO

(DJ Mo1·h number ..•.•..•••• . . ••• 0. 655

(£) £PR • • . • . . . . . . . . . . • . • • . • • 2. 35

SAMPLE LONG RANGE CRUISE­MACH NUMBER AND EPR

long Range Cruise-Nautical Miles per Pound of Fuel

(For fli;uro 11 -26)

(fJ A\'eragc ~ross weight . . • • .... , • 18.000 lb

(CJ Pressure nlliiudo •••• .••.••.•• 25,000 fl

( ti ) Temperature devlmton Crom ICAO standard (Ambtent tempera-lure • ... 24, 5~(.' ) , ... , ..•.•• , • , 10 c

(J) Dr;ig llldcx . .... ... . . . . . . .. . 100

(K) Prci:;suru :tltitudc ..• ..•.. .• , •• 25,000ft

(1..) Ambient tcll'lp~r,ature , . • . . • . . • . -24. 5 ~C

(M) Nauurul mllea per pounll or ruel • • . O. t50

11-46

SAMPLE LONG RANGE CRU ISE­NAUTICA L MILES PER POUND OF FUEL

MAXIMUM RANGE CRUISE

Maximum Ran~c Cruise chttrts. shown in f~urea ll·27, 11-28. ;t_nd 11·29. present the n('ccssnrv mission plrmning d:1ta to set up maximum ran~C cruise schedules for a const:int cruise altitude. To I use the maximum r•tnge rharts, the :tveJ':tge gross wetght. CJ'UiSC altitude, drtlH index , ~ntbtf'nl :1ir 1emper:1ture. rcl:.ti\!C wlnd . :md ~round d1st:1ncc to he covered mul'Ot tw known. It is then possible to determine trut! M;1ch number. true :'llrspecd. lime enroutc. oautic!al miles per pound or fuel. fuel Clow , ar.d total fuel required. Optimum <-..tu1se a.lt1tudo (altitude for Uesl r;Ulge) lines ;trc superimposed on the J)rC$8ure :1Uitude plot.

SAMPLE PROBLEM

MaJ<imum Range Cruise - Time and Speed

(For Cl~uro l 1-27)

(A) Avcrngc g ross wei~ht for crul:;c leg, .• , ..... . 18.000 lb

... 26 0 z 5 24 ... § 22

.. :z: 20 C> ... ~

~ 0 ::; 16

... ~ 14 .. ~ ' 12

.9

.8

: .7 ID :E ::> :z: :z: u ~ .5

w ~ .4 ..

.3

M ODEL: A·4M ENGINE: J52·P· 408

.2

NAVAI.R Ol -40AVM- 1 Section XI Part 4

Section Xl Pa:t·t 4

NAVAIB Ol-40AVM- 1

MAXIMUM RANGE CRUISE MAXIMUM RANGE CRUISE TIME AND SPEED NAUTICAL MILES PER POUND OF FUEL

MODEL: A·4M DATA AS OF: 15 OCTOBER 1971 PRESSURE

OPTIMUM CRUISE ALTITUDE AT DRAG INDEX

I 0 100 ::: 200 ...

80

70

60

so

DATA AS OF: 15 OCTOHR 1971 DATA llASIS: ESTIMATED

... 26 0 z ::> ~ 24

§ 22

ENGINE< J52- P· 408 DATA BASIS: ESTIMATED

OPTIMUM CRUISE ALTITUDE AT DRAG INDEX

0 L..Gl----- 100

1-o-'-l--l.-- -200

ALTITUDE -1000 FT.

0 5

10 15 20 25 30 35 40

SPECIFIC RANGE

ICAO STANDARD TEMP. - ° C

15.0 5 .1

-4.8 -14.7 - 24.6 - 34.5 -44.4 - 54.3 - 56.5

::> z - NAUTICAL MILES PER POUND OF FUEL

t 40 .05 .10 .1) .:lU .25 .30 .~) .40

I ... :E ;:

t I I I

20 I _ _, lO

0

50 0 -50 -100 200 250 300 350 400 450 500

AMBIENT AIR MAXIMUM RANGE TRUE AIRSPEED - KNOTS TEMPERATURE

- •c FA1·160

FAl-169

Figure 11- 27 . Maximum .Range Cruise- Time and Speed F igure 11-28. Maximum Range Cruise- Nautical Miles per Pound ol Fuel 11-47 11- 48

"' 0 z ::>

~

0 ... "' 5 5? "'

8

7

6

5

4

3

2

NAVAlR Ol-40AVM-l

MAXIMUM RANGE CRUISE FUEL

Section XI Part 4

MODEL: A-4M ENGINE: J52- P-·408

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

10 ~ 1----0 - I I

.40

u: ~ .35

0 0 .30 z

IM::> ~~ .25

~= uA. .20 ii:V> u~

~i .... i5 ;:: .10

~ I .05

0 0 1000

I I I I

I \ «' c;. I 11,_~1' I ~Ofo~I co~~\,

2000

or I I

3000 4000 5000

FUEL FLOW - POUNDS PER HOUR

Figure ll- 29 . .Maximum Range Cruise - F uel

6000 7000

FAl -170

11-49

St.>t:tiou XI Pai·l 4

NAVAln 01-40AVM-l

(Ill Crui se nltltude.

(C) Or:\~ inclt·~. . . • . • . •

{0) Tnw M:t('h m1mbcr • .... ,

(€) Am,>icnt :\I I" tempera.lure al °'"'"" .oltitudo (ICAO ~Lllnclard

I tClllJ)Cr'3U1re JQOC).

(F) True airspeed • • • . . . . .

! (Cl Tnilwind.

~ (H) Gmund di~t~ncc ••

G

25. 000 rt

100

0.615

-24. s0 c

380 kn

SO kn

200 NMI

! (,I) 1"1m• ••.••••• . •... 28.0 m:n

I

I !

I

11-50

SAMPLE MAXIMUM RAN GE CRUISE-TIME AND SPEED

Maximum Rang e Cruise- Nau tical Miles pe r ~ Pound of Fue l

i (For ligUJ"(" I 1 ·28)

(Kl A\ct.lt;ti ~Toss wcl~bt. 18. 000 llJ

(I..) Cruise nltltuue . 25. coo ft tr I .

(M) Tem1>c r3tu1-c d!!viation frum ;. JCAO standard (Am,JlPnl r tempoJ-atui·c -24 . soci 10°c I

' ~ (NJ Ora~ lndcx. 100 '· 0

(Pl Crul~• nllltud<· . 25. 000 II

'J (Q) Ambient temperature • -24. soc I

d (R) Nautor:tl mllcsp<rpoundofluul. 0 152 N\11 lu !

SAMPLE MAXIMUM RANGE CR~ ISE- ~ NAUTICA L MI LE S PER POUND OF FUEL ~

I I

I I I !

FA\·l'H W

NAVAIH 01-40AVi\l-I Section XI P;lrl 4

~ Maximum Rang e Cruise - Fue l

! ~outteal rmlt·~ pi•r pound nf fuel •••• .• • .• I

(S)

(T) Ma'.\1mu111 r.:mg.- Lnu" :ur8J>eed

(W) Fuel !low

0.152 N~fl 'Jh

380 KTAS

2500 lb hr

! !

l

(X) Time .. 28.0 mln

(Y) Tot:ot fool r<!qulred . 1170 lb

SAMPLE MA XIMUM RANGE CRUISE - FUEL

r11.1-1!.&

II NAUTICAL MILES PER POUND OF FUEL

N011ll<"al \ lilcs por Pound of Fuel ch01·t s (figure 11-30. hhtwh J th1·Qul!h 6) )Jretj:ent rrulse data

i lhro~houl the $tru"°' weighl. ni rspeed. and dra~ Index ran~c or the ni1·e1-n!l. Thc&o d;:1lfl arc p re­~cnled for US<' when crutse d:ua nre required Cor

f::t :;peed rond1tmnn t>lht r lh;m milxlmum range or long II r ;mp;e cruise. ·ro usa Lite NauLic:tl Milos per Pound

of Fuel charts. tht! aver.al~~ g:ros5 wct~ht. 1u·c~~ur( I '1ltlludc. cruise l\t:u·h num'Jer. drJg Index. :ind B :uubtenL :Ur tempc1'3lurc n1uhl lH-' known, I t \5 then I 1.>n:,sible to determine true nh·:ipo:ed, naulit'••l milt1~ 1>cr 1>0und of fuel. fuel flow. :tnd cn!,llnc ptCS!->un

1·:tt10. It is J'C:commPndt>d 1hac cngfnc pre~surc l'::ttio I be U.!!:~d as the prlm:u·y O\<!asurcnwnl nf 1•ndm:• lhrmct oulput r:1 lh ttr lh~Hl h •el flO'l' when ~Cllinq UIJ cruiN<'

schc<lules. ! SAMPLE PROBLEM

Nautical Miles per Pou nd of Fuel

(For r!~'IJrc 11 -30. •ho••l I )

(A)

(B) Cruise pressure altitude

(CJ D1·aK 111dcx = 0 (b:.tt(.)lifle)

(I)) Cruise \Jach number .

(E) Thrust 1·enuin·d h ;1111'.;t clean al remit • • • . .

SAMPLE NAUTIC AL MILES PER POU ND OF FUEL

! 14. 000 lb

30. 000 h

0. iS

6225

·I

11-51

Section XI Part4

NAVAIB Ol -40AVM-1

NAUTICAL MILES PER POUND Of FUEL

MODEL: A-4M ENGINE: J52-P-408 10---~~ ....

20

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

MACH NUMBER FOR MAXIMUM RANGE CRUISE AT DRAG INDEX

0 100

s

6

7

9

10

11

12

.D E 0

~ ... .. s ~ .. ... "' ::> .. :i:: .... t: ~ v .. ;;; z ~ d

.2 .3 •• .s .6 .7 .8 13

.9

TRUE MACH NUMBER

"' c 26 z ::> 0 Q. 24

~ 22

.... :r !2

20

~ 18 ... "' 0 .. 16 I)

:; ~ 14

~ < 12

FA l - 171

Figure ll- 30. Nautical Miles per Pound of Fuel (Sheet 1)

11- 52

.0 E

,,,o

a ... .. ;:; a ... .. :;; "' .. :z: ... t: ~ v .. < z ~ v

::: .. :i:

"' z :z: v < :i: ... "' .. ...

12

13

.9

.8

.7

.6

.s

.4

.3

.2

NAVA!R Ot-40 AVM-l

NAUTICAL MILES PER POUND OF FUEL

Section XI Part 4

MODELt A·4M ENGINE: JS2- P-408

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

FAl-172

F igure 11-30. Nautical Mile s per Pound of Fuel (Sheet 2) 11-53

I

Section XI Pai·t 4

NA VAill Ol -40A VM-1

NAUTICAL MILES PER POUND OF FUEL

MODEL: A·4M DATA AS OF: 15 OCTOBER 1971 ENGINE: JS2-P-408 DATA BASIS: ESTIMATED

.8 ~ "'~ "'"'"'"'~"'~ "'~ ~"'"'"'"'~

... "' "'

.7

.6

.s

.4

.3

.2

40

30

20

10

0

~ - 10 ... ... ~ -20 .. < -30

~ -40

~ <

-50

-60

-70

-eo

11- 54

NO REYNOLDS NUMBER EFFECT ON FUEL FLOW

FA1 · 173

Figure 11-30. Nautical Miles per Pound o f Fuel (Sheet 3)

NAVALR Ol-40AVM- l

NAUTICAL MILES PER POUND OF FUEL

Section XI Parl4

MODfl: A·4M ENGINE: J52- P-408

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

12

"' 11 0 z :::> ~ 10

... E 0 .. -. s

"' 5 0 ... .. t; :::>

"' :z: ...

~

8

7

6

5

4

3

2

10

2 3 4 6 7 GENERALIZED FUEL FLOW PARAMETER (UNCORRECTED FOR RNll

fAl-174

Figure 11-30. Nautical Miles per Pound of Fuel (Sheet 4) 11-55

I

Section XI Part 4

10

2

MODEL: A-4M ENGINE: J52-P-408

NAVAJR Ol - 40AVM- 1

NAUTICAL MIUS PER POUND OF FUEL

DATA AS OF: 15 OCTOBER 1971 DA TA BASIS: ESTIMATED

PRESSURE ICAO ALTITUDE STANDARD

- 1000 FT. TEMP. - •c 0 l S.O s 5.1

10 -4.8 IS -14.7 20 -24.6 25 - 34.5 30 -44.4 3S' -S4.3 40 - 56.5 4S -56.S

.so

.45

.40

.3S

.30

.25

.20

.IS

.10

50 25 0

0 -25 -50 - 75

AMBIENT AIR TEMPERATURE

~ ... :::> ... ... 0 0 z :::> 0 ... .. ... ... "' ~ ~

5 ;:: :::> ~ z

-•c fAl - 175

Figure 11- 30. Nautical Miles per Pound of Fuel (Sheet 5) 11-56

: .. :e :> z

.9

.8

.7

.3

.2

.50

.45

NAVAffi Ol- 40AVM- 1

NAUTICAL MILES PER POUND OF FUEL

MODEL: A·4M ENGINE: J52-P-408

DATA AS Of: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

200 300 400 600 TRUE AIRSPEED - KNOTS

Figure 11- 30. Nautical Miles per Pound of Fuel (Sheet 6)

Section XI Par t 4

fAl - 176

11-57

I

~

I I

Section XI Part 4

No uticol Miles per Po und of Fuel

(For f11,'Ure 11-30, sheet 2)

(F) Tllrusl required A omu -clean nircrn!t . . . .

I (II) Drag rndex • . . • .

~ (,J) Tot.a.I thrust requ1 red1 6 anib

! SAMPLE NAUTICAL MILES PER POUND OF FUEL

No uticol Miles per Pound of Fuel

I (For lib'Ure 11-30. sheet 3)

(K) AmUlenL .1ir lempcr atur e •

(L) Pressure :tltltude . .

(M) Crui8e Mach m1mber •

(N) Reynolds number L'1dex (Rr<1)

11-58

NAVAIR 01·40AVM-I

6225

0 . 7S

JOO

8820

30.000 ' t

0 . 7$

o. 503

SAMPLE NAUTICAL MILES PER POUND OF FUEL

Nauticol Miles per Po und of Fue l

(For flJM'e 11- 30. sheet 4)

(P) Tot:tl thrust required, ~ amb 8~20 lh

(Q) Cruise Mach number .. , . O. 7S

(R) Gener alized fuel flow µnramctcr (uncor rected for ReynoJds number effect) , • . . • . 6. 23

(S) Reynolds number Index (RNJJ • . O. 503

(T) G<!llerallzed fuel flow par~metcr (corrected for Hcyuolds number effect) • • • • • 6. 41

~

I .1

I I

I

I

SAMPLE NAUTICAL MILES PER POUND OF FUEL

Noutical Miles per Pound of Fu el

( l'or Cl1tUrc ll -30. •hect 5)

I (Ul Gencroltzcd Cucl rtow

parameter (corrected ror Hcynold6 numher eUect)

(V) t"rulsc Mach 11umbc1· •

I (W) Pressure ~llitlldo • ,

(X) Ambient 1dr 1ernpcrature .

(Y) ~aul ital mtle5 JM"r

NAVAJll 0 1-40AVM·l Section XI P-..t rl 4

G. 41

o. 75

30.000 (I

SAMPLE NAUTICAL MILES PER POUND OF FUEL

Nautical M ile s pe r Pou nd of Fuel

(l'or rt1?urc t l-30. sheet Gl

(A) TJ•ue Mach numl~r , . . . , • . . O. 75

(0) Amb1ent ,,ir tcm1>cratul'e . . • • . . -44. 4oc

I 1'°'1nri ur Cu•I • • • • • . • • • • . O. 174 (C) T rue :urspeed . . . . . . • . . . H2 kn

l t-59

Sec tion Xl P;irt 4

Nautical miJes per pound or [ue l

Fuel now

11- 60

SAMPLE NAUTICAL MILES PER POUND OF FUEL

NAVAIR Ol-40AVM-t

0.174

2550 lb/ hr

SAMPLE PROBLEM

Engine Pressure Ratio for Cruise

( Fo r llgur e 11-31)

( F') Total thrust requi red/ A nmb

(G) True l\.fach numbe r

(II) Engine pressure rntto

SAMPLE ENGINE PRESSURE RATIO FOR CRUISE

~----········-··-

8820 lb

0 . 75

2. 55

I r: d

g

!

l

I

"' 0 z ::> 0 ...

J> E D ... .... s

"' 3 2 "' t; ::> .. :c ... g ...

NAVAffi 01-40AVM- l

ENGINE PRESSURE RATIO FOR CRUISE

Seclior. XI Part 4

MODEL: A -4M ENGINE: JS2- P-408

DATA AS O F: 15 OCTOBER 1971 DATA BA SIS: ESTIMATED

14

13

12

11

10

9

7

6

5

3

0 1.0

f 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 2.8 3.0

ENGINE PRESSURE RATIO - P1,f P10

Figure 11-31. Engine Pressure Ratio for Cruise

3.2 3.4 3.6

FAl - 177

11-61/ (11-62 blank)

I

NAVAJH 01-40AVM-l Section Kl Part 5

PART 5 ENDURANCE

FOULED DECK ENDURANCE

Occasions arise during carrier operations when the deck becomes fouled and airc raft c ;:innol be t;tken aboard until lhc deck is clca1·ed. tn Lhesc insta:1ces. u ts <tes1ra.01e tor tne puots anci tile a ir 0111ccr to be aware o! the endurance capabilities or the unrc­cover ed ai rt raft so that an 1mmediate decision ;:;m be inade concc1·ning the proper course of action. Should the estimated "clear deck" time be bcyot1d tl1c

I endurance time or the alrcrait. then lt must either depar t immediately for the beach. or land aboard the ready deck of another ca1·rier. i! available .

! However. if it i11 either des1r:ible or m~u1dalory that the alrcralt orbit until the deck is clear. it is necessary that the pilot fully undc-rstand the proper procedure to obtain the maximum endurance with the ::i,vailah1e fueJ. 'the fouled Deck Endurance chtlrt (ligure 11-32) tabulates the endur•nce limes for v3.rious quantities or fuel OI\ board a t both the i11itial ~\ltitude and the optimum, best endurance altitude . The :tir c rart <:on£igura.tion COn8t8lls of four empty wing J)yl oos plus ~ns wilh a total drag i ndex of 33. The endurance v:llucs arc given in minutes: for Lhe optimum altitudes include the time required for a military thrust climb to that altitude and a maximum r aoge descent to sea l evel with 250 pOt.mds of fuel remaining for approach and Landing. 'The clldurancc time~ for the initial altitude include only the descent t ltne since no climb ls required . Climb speeds and airspeeds for m3.Ximum e11dutance a r·e included in the chart together with letdown instructions .

I The time at which letdown should be inttiated is g iven in terms of fuel on board and represents I.he fuel requir·ed to conduct a maximum range descent from altitude to sea level. A 250-p<>und fuel allow­ance ts hlc!udcd tor approach and landing.

I Bingo Endurance and B ingo Endurance- Gear 0()YJn charts arc presented ln llgures 11-33 and 11-3{ respectively. These charts are provided for an ni rc raft confi(fllr ation consisting of four winu pylons. guns, and two 300 .. gallon external fuel tanks wi:h a total drag in<lex of 61 with gear up and 391 with gear down. The procedures for the use or the charts are

identical to those (or the Fouled neck F.ndur::uH't' chart; however. an 8QQ.p0und fuel allowance is included for approach and landing.

MAXIMUM ENDURANCE

The Ma.xiznum F.11durancc charts ptovidc a 1'ncani; of detcrmininJ: the M ach num~r ruld calibrated air .. speed fo1· maximum endurance with the associated fuel How and fuel required for a s1>ecllied loite r time . 'rhese <l:atn are provided for ~t constant :1ltitude loiter condition. Optimum loiter altitude lines. allitude for best endurance arc sul)('r imposed on the ptcssurc ahltude plots. To use these char ts. the average gr oss weight. b;mk ;rngle, p ressure ;ll tilude. drag index. ambient air temperature. and loiter time must be known. The charts then provide M:ich num ­ber. calibrated airspeed. fuel flow . and fuel r equ ired for maximum endur~Ulce.

SAMPLE PROBLEM

Moximum End uron te Speed

(For !if,'Ure 11- 35)

(A) Average gross weight 15. 000 lb

(B) Bank angle . . . . 15 degrees

(C) Loiter pressure :iltltude 25, 000 It

(D) Drag index 100

(E) Mach number for maximum endurance 0. 475

IJ-63

!

I I I 1

w

Section XI Part 5

NAVAIR 01·40AVM· I

lk3JC Index 33 A1rcr:\ft \\>\•1~bl (Ll•Ss Fuel) 12, 039 l•ouudio

All P) Lons and Cu.nt. (?-:u Ammo) ll.<'jle-rt <' f\1el tor L."\nding 2;;0 Pounds

).tod1.•I: A-tM Ens:in .. •: J.;2-P-oJO"

n~u:t M <If: l D<'c<'tnbl"r WiO O:it:> n!'l~i e:: l·"Ntim~h"I

Jo..;ndurrutc:1._•

"' S<-a L<'\i{•I

t:1.dur9.m:t•

~t1 mum Optimun1 Altitude- Altilude

If \'oo .\1•c at JO, 000 l'l·d

Endurance at

10. 000 Fe<>l

:\hnuh.•s

~~n<hll':ln('('

"' Oplimu1H OpliO\um Alhtudl' AllJtud1..·

Minuh.·~ i-'1._•cl

If \'w ,\ 1•1._· al 20. 000 F('(•l

1~~ntlu 1'211~<'

"' 20,000 } 'l'(.'l

Minutcti

OpUmum Opli mum .\Jtiludl• All1luth.'

~linuh.'fl l'r<>t

2100 1---"-;--1--'-"---1--'3_s:...,o..co.:.o--1--;:..:'-+--':..:"-~:-:3.:.;:..:,ooo~+-_:.sa:..__1--......:D~3:..__i_:3=•~·oo:.:.:o_ 1~>00 1---:-:-+-G.,."---1-3-s.;...o_o.;.o-f--'-::;9'--l--·-',3---"f--'3-'G'-,o-'o-'o+--;0:_~1---':..:'--1-=".:.;;:..:• oo.:..:.o_ l•VU 1-----t--":...'"---1--'"-'":...· •.;..•.:.•--1---"""~·-+--•:..:'''----"f--'3.:.;:..:•oo~o+--=63=---~1--_:G:..:D_-1_:".:.S~,O~O.:.O_ ~~:1---3.,.G_-t-_s_,_--1_3_5.;..,o_o.;.o-t--4G'--l--5'-r.---"f--'3-'S'-, oo:.:..:.o+--'-",:__:1--_:r.:..:'o_-l_;3.:.5:..:·o:.:o.:.o_

1---"-"-+-4_.1 _ _,_a_s_.oo_o-f--'-3n __ 1--·-"---":-:3.:.s:....oo:..:.:..:o+--•':..:_-1-__ :;:.:2_:-1_:3.:.:;:..:•oo:.:..:.o_ :n J 100 2.i 3~ 35. ooo sa so :lS. ooo 10 rn 3,:,, ooo

J 900 ~====J=9 ==~~=="=·a===~==3=•=· o=-o_o-t - __ ir;-_. -+--"-o- -i__,"_:;_. o_o_o+ __ :u _ __,.__3_r. _ _._J_s:..., oo_o_ 1 700 1---1~3-+-~"---1-3_0;,,;,o_oo.;._-1---''D'--l---'2:.:2'----"-'-3:..:s:..:,oo:..:.:..:o+--=2~:.._~1--_:2:..:c.:._--1_:3=:;:..:•(:..:~.:.o~ ~ :,oo 1-----'---' o _ _,_1_s_.o_o_n-+--12 __ .__1_3 _ _,_z_s_.o_o_o+--'--' _ ..L _ _ 1_1 _ _t_3_0_.o_o_o_ ~ If Yw Arc tH 30. OUO Fc:d

En<luranc<-• al

30,000 f'('N

Erdurancc al

Opt1m~1m Altilud<.•

OplJtnum ·\ltitudc

EnilUl':tnCl' .. 3G .OOO

Fe(.'\

Minull'l:i

Endur:tn<'<' ., Ophmum O~imum .\ll1llHlc .\ltiludc

Minulcio l"<-'<'L

If You ,\1'(' :u io. 000 l'('('I

l-'.ndUr:tl1('f'

at 4.0, 000

.. ~\_'(.'l

,\linut.ci>

1·~-':IJ1('(' at

Opl.imum O(ltintum .\llJtmlc .\ltiludt.•

t\llnulct> l't><'~ I I

2:100 1---"-a _ _... __ !JG_ 3:;,0-0-'-o-+--'-s·_, --+--9'-;--l-'3,;,,;;..;, o-'o,;,,0-1--..,;,,9"..c• --1--:..:9:.:9_-l._:3.:.•·:..:o.:.o.:.o_ 1900 'i~ "'(I :J=i.000 M ~1 3.>.000 ~2 't3 3S,OOO

1;oo t--~,-o---t--~,2--1-3~:;-,oo:-:---o--l--1-a--+--1-:t---!l--,'-r,,;,,. o'-o"'"o+--'-1.:.4_-l·--,:..:s:-;--1_:3:.:5.:.,o:.:o:.:o_

I ljOO~====r,=2=======r.•===~==:t=•=.o=o=o=:====r.=s===:===·=·5====~=3=;=,o=o=o=:====G=G===~===•;·•===~==3~:;=,o;o~o== 11001---"-'-~-·-·•---;_3_:;,;,,,o_o~o--1--'-'-;-+--":..:-'---11--3:.::;.:.,o:..:o.:.o+_...:..:.'-.:.'_-+-__ •:.:· '--1_:3~;.:.. o:.:o:.:o~ 1100 .J:; 17 _L3:;,_0_00 __ 1-_ 4_• _ _. __ ·1_•_-+-'-3:;_._o_oo_. __ ._w_-+----'' .:.9_ -1-....:..'":.:":.:o:..:oo:.._

0001--~3_;_-l-_3.:.':..:.:..: _ __:3:.:;,;,,. oo-'-'o--l--=3.:.u_+--'~'u'----"f--'3=:;.:.· o:..:o.:.o+-_:·•.:.•_-+---·.:.":._-1_:3:.:5.:.,oo:.::.:o~ ioo 1---'-u-+_,_u_~_:1_.;_. oo_o-1 _ _;3,;,,.1 3 1 3~_._o_o_o_,_ __ 34? _ _, 32 3~.ooo I soo 20 20 3.;, 000 22 t2 3:;,000 2:1 23 a • . ooo

! --'-"-'==--+---""""c;:.:,oc..:.;~;;,;_---l---":C.:"'---'-1---"'~ll~c~•c~· c~"'~'~Spc~·~<~~,,,,_--l---'::.!!!S~'~~·~·l~l.~c·~W~o•~n"'-""'---Pr('~Jolurl• Climb ::,peed Endura.rK·~~ Ell(;l1l(' Idle - 1''nm1 .\ltilud1.· .\ltitmf<> '.\lihtal'\' Tht'l 1~1 Soced S1>..'C<lbraJ.(.•f. Clos .. '(( \V1lh .t'u .. •l lh'mauliru:.

I F('('t r-C.\$ Mo.th :\!,). KC.\l) t\C:AS Pound!>

St>n 1"'''"1 :.ir.; 1'~ 1sr: 2r,o :'If.~ "r. J~~ ----1-----J.""-''-1 __ _

10 000 _3Gl l~!l l>.!5 292 1a oou 3(;;-, 1"5 1 .. a 30;

i~ ~~~ 36~ - ,,-, 7"'•"'3---!--!--17',~7~---+----:;.;~.:;;~----1-----"~"'~~'-. ---

1 :iii~ -+----_-+--~;;-'~-=i""~,,.~"---_-_--!+_-_-_-_-_·--'-'1"'-_,~""~"-.::::::::.-:'~::::::::::::::.:t1c:~"';~"'-~"---_-_-_-_-_-_-_,+_-_-_-_-_-_-_-_-_-,,,_~"'l~"':"·~:~_~~--~~--~~-Figu1·e 11-32. Fooled Deck Endurance

11-64

NAVAIH Ot-40AVM·I

BJ}:(;() E?\-OURAXCE

Or :11t l.l'lde"< (.t All'f:ralt WQl,<ht ( Less f'uel) • 12, 437 Pound.ti

AU !>)Ions , Cuns (Nu Ammo), CUld ·r wo 300·G:>.llon t.:xtcrn.al TankR Hc.serv~ F\l.el for IA.nding 800 P ounds

~Ct!On XI Pa.rt 5

Model: A··lM l.~tlg.iuc: J:i2-p-i1os

Ont.:t :tJ1 o!! 1 Dcccmtx·r- 1970 D::ita BG.Sis: Esllm3.l('d

~

1 c. I

1 a ,; ,'.!

EndUr:tnC<' at S(!a. Lc\•('J

MIJ1UlNI

2700 50 1.500 45 2300 •10 2100 35 1900 2~

1700 24 1600 19 1300 J•I HOO •

Endlll':tnC~ al 30,000

Feel

1'11n11lt's

2700 >0 2$00 73 2300 GB 2100 5~ 1900 !'11 1700 44 1500 3fo 1300 29 1100 21

Ptessurl" 1\llJwdf'

ll You Ato at ~:ll.C\'CI

Endurance a.1 Optimum Optimum

AltiW<lo Altitude

!\Unut~s J•'f'N

70 3f'1. noo ,,, 35 OOD 56 35 000 4> 35 000 42 3~ 000

~~-4~~~ l• 30,000· 0 1:> Ooo

U You ArP at 30, 000 f'tOl

Enduran.c.-Ill Opumum Opthnum

Alt.true.le Altiut.:le - -.MinutCJi Fe<>I

82 35,000 75 35,000 67 35, 000 ao 3G.OOO .52 35. 000 44 35,000 37 35,000 20 35.000 21 30.000 .._ - -

Climb Spc<~ Mllttnry Thnuu

Er.dunuu:c :11 10. 000

FC!<ll

Ntnuws

t.2

'" 50 H 38 32

~g )9

13

£r-dur:mcc ru3.5,000

Fet:t

.MinuU~.3

83 76 69 ., "" •G 38 30 22

If You Arc nt 10, 000 F~l

Endul'nnr'<' .Endurance at Optimum Optimu m "'20, 000

Altitude Ahitude t·cct

Mlnutt'9 Feet Minules

14 35 000 n C7 "' nnn "" GO 35 000 59 o2 30. 000 r.1 45 3; 000 •6 ,, 3:.i.DOD 39

~~ -t-.3:; , 000 32 33. 000 25

I• 20 000 l<

l( You Are at 35. 000 l''CCl

Endurnm:c F:ndUMVl('(' ru OpUnnnn 0 1xtmvm nl <J0,000

t\ltim<lt> Altitude •·eel - ..... Minutes Jl"cet 1'Unl.lte¥

83 35.000 SI 76 3o. OOO ,.. 09 3n,ooo 67 t.l 35. 000 r.o 54 35. 000 53 46 3:;, 000 ·16 3o 3.;,000 3fj

30 3j,000 31 22 35, 000 23 ~

J)('.i;:ccnl Speed tnbrinc 1dk­

~"pc«tbr;tkc.s Cloa.t.'tl

J( You Ar-e Bl 20,000 Feet

Endur:mcc m Optimum Oplimum

AIUtudo AlUtude

Minut('ll F<"N .. °' nM

' 1'.000 04 30 000 Ga ~~:.J.Q.C!L_ ·19 30 000 .. 35 000 33 35 000 2l 3&. 000 7 30.oon

JI You \1·c nl l0, 000 fee'

Endu1·ance nt Opcfnu1m Oplimum

AIUt.udc AlUtuW.:

fl.IJnutcs ft.'C\ .... s; 3G, 000 71 35, 000 70 :rn.ooo ~3 35. 000 SG 36,000 17 a• .ooo 39 3:".,000 32 35. 000 2•1 35.000

Stnrt l.cJ.dO\\TI l.- rom Alllt.udc

Wilh l"ucl lkm:uulntit

f('<.•t KCAS .Mnoh N'o. KCAS KC.'\S Pound.I!! - 1-

Sn Lc\•cJ 340 J9() 187 soo ~

5, 000 340 100 187 S23

10, 000 340 l~O -1----'l:..:•.;.7 ____ !-___ ...;S..:.39;_ __ _

IG,000 3·10 190 18:7 SS3

__.:2.:;0•:.:0..:,00:__!-_;3:..:·10:__.j._ ____ 4

__ J!)() 18'7 -t- __ SG_7 ___ _ 2s. ooo o. 76·1 lOO 1S7 s<o

~-...;30~·~00..:.0;__1-----+~-""0.7~~..:,1_-+--~100'-'----+----~1~8-~'-----!l---·~-~89~2.._ _ _ _ 35, 000 _ ~: i'£!_ J90 lS7 ~11 W , 000 O. 7CH 190 1~7 OJ:i

.J5. 1)00 0 . 1r,a 190 187 927

Figure 11-33. Dingo Endur:ince

11-65

~

Section XI Par t 5

NAVAIR 01-40AVM-l

Urug lnJ...1x :ml .\ircn1f1 \\c1~ht (Leu l"ucl) 12, 1:17 l '\Juncf!'i

\II I.., luM, c;un~ f~o .\1111h•1), .m.J 1''11.u :1Vll··(;;dlon r :-;1eni;,I Ta,,kfO Jksc.•nf' l"ut>) fol' l..1n•lln~ .,tl!I l'()un\I~

I I

I \ln.tld .\- D l f:nRi••" J:;:' -i'-111>

~

!:n•lur.11u•'-' al ~·a

L~'\t·l ,__ ____ _ Jo:ndurnnc."(I al Qvtnnum

All1lu•Ju 011llmum ASutmJi.:

rnrlunlflc'(' al 10,uoo

F1•N

l>,tl;\ a.a 1•f: I l'<'l·l·mlll'r 11J7U t>.tt~ R1.:;:1i.: l1111n.1trd

Ir Yvu An' :tt lO. 111•~1 ..... , ••

J..n,lui"1.nt:t.· a 1 (1pc 1t11u111 ormmu"'

\1ti1vil1· 1 .\llitu•k·

I

1 .. I

i :

l .IUIJ

l 101I

~ Z'iCth

.;:~(.>IJ

23011

~lUU

t !tOO

);'110

1·.1111

l'.Hk)

lll!<J

'"

I 2•

I+--': . a.,

II

Jo;uJu11UJ~t·

at 20.001)

.f('("l

.\lrnult!~

:\ll.nutm•

I -13

2 .. _,_

12

I 1 , 'Iott

Iv, UQO

)1•.ll()lt

,, '"

~I

1- ·~ JO

~~,--11 -f'.'ndur:1nt•(' Fn,lur..irH.:(: l':ndu1 .n1..:\

Ul Optimum Optin1um Ill JO,M>u 1U Optlmu111 Ahlt.udt.: \ltitu!J11 fi'N \hltu<i1 l1lnu1e--.--~--,,.,-,-.,--+---:,-,.ll,_n-uw-,--+--~:-;l,-ln-utc~

-

..:u, liO!t

4.l11tlmum 1\ltltt.111\'

-I-----~-.._--~ ,·, ..

ou 51J !?;";, t)l)I! .)~ .J.:1 :!.;.,, 01111

.J:t l j :!:i,01111 Ii I.. 2:;,01ttJ

,_ ___ 4•-' -----,---'-"---r---~2:~··-•_01_• -+----•~"---+---'-a __ _,.• __ 2_j~·-"'-'o_ f- ~n --~---"-•---1---2;-",. Qo•.! :ti I :_t.;,uo~J l----·"-'----i---J4J !.?O,On(I :.!:! 1~

f---~2~'---1--- 24 _2'~'·-"-"'-'-+----~-;---+~ '.!U,dO!I

'!i .::1, l!lld

1n ~---r------~·-1 - ,,; I J IJ :.!IJ.U\f•J Iii 2.11 11110

------'------~'--------'-------'---~ r~.sl'rnt ~ll('•'•' :-1:. rt l.c1<tim n

J>r1•t-lt\ll'-' Cllmll ~'4..'l'd t.r~lurtt!H.'t.' Lnl:illl.' hllc ! r«.im .\ltllu•I<

Altltu1..;~..;' --+---"...:11_11_"°...:'_Tl.:..•;,:,n.:..' ":...'--+---''-'r~,;,·<.:.."-' ---,,---""'''-'"-''-''"-''-~'-''_<_'l_"_''-"1--T--\\ 11 h l tll'I HC'nualnlni.:,

S.-riJ.<"\f'I

t , iJf10

l U.VVO

...,0,flOU

.. 0,01J()

_.10.vuo

11-66

1n:.

~o • ~----+--~~

11in

llill

l •iO

lfiO

l!Hl

1 •~··

F'igul"e J l-34. Bingo Endu r;1nce - Gear Down

.....

.70

.65

.60

.55 ::: .. ~ .50 z 0 .45

~ .... 40 :::> • ~

.35

.30

.25

.20

MODEL1 A-4M ENGINE: J52-P-408

NAVAIR Ol-40AVM-l

MAXIMUM ENDURANCE SPEED

Section XI Part 5

DATA AS Of1 1S DECEMIER 1971 DATA BASIS: ESTIMATED

~\_ 26 ~

~:: ! ...

18

16

~ 0 ac

" 14 ~ 12

50 25 0 BANK ANGLE - DEGREES

... > "'

I 00 150 200 250 300 350 400 450 500

CALIUATED AIRSPEED - KNOTS

FA1· 180

1''igure 11- 35. Mrudmum Endw·:ince Speed

11- 67

Section lG Part 5

NAVAIR 01 -40AVM-I

(F) Loller pressure altitude 25, 000 fl SAMPLE MAXIMUM ENDURANCE FUEL

(C) Loiter airspeed • • • • 195 KCAS

SAMPLE MAXIMUM ENDURANCE SPEED

(K) Bank angle 15 degrees

FA1•176 (L) Louer pressure altitude 25, 000 ft

(M) Temperature deviation lrom ICAO standud (Ambient temperature • -24 . 50C) .. 10°c

IN) Drag index 100 SAMPLE PROBLEM

(P) Loiter pressure altitude 25, 000 ll

Maximum Endurance Fuel :Ql Ambient air temper~uure . -24. soc

(For !lgure 11-36) :R) Fuel now . 1900 lb/ hr

(S) Lotter tt01e 30 min

(H) Average gross weight 15,000lb (T) F'\lel r-equired . 950 lb

11-68

MODEL: A-4M ENGINE: J52·P-408

PRESSURE ALTITUDE - 1000 FT

u 5

10 15 20 25 30 35 40

ICAO STANDARD IEMP. - °C

15.0 5.1

- 4.8 -14.7 - 24.6 -34.5 -44.4 -54.3 - 56.5

NAVAIR 01- 40AVM-l Section XI Part 5

MAXIMUM ENDURANCE FUEL

4,

.. 0 <

!'<'--+--.-........ % 25

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

2000 4000

... Ci IAS Wiii! 'i ~so, ~-.L--+--..L...;;.;..c.'-'-'-..:..:.;"-'--....i.~

FAl-181

Figure 11-36. MllXimum Endurance Fuel

ll-G9/(ll-70 blank)

I I

I

NAVAJR 0I-40AVM-l

PART 6

AIR REFUELING

Seclion XI Part 6

AIR REFUELING CHARTS SAMPLE 1 ANKER SPEED ENVELOPE

The air reruellng charts present the pertormance of a tanker confib~red with an air-r·efoeHng buddy store on the centerline pylon, Cour wing pyl01lS, two 300-gallon external fuel tanks, and two 20mm guns. All performance darn shown are based on an ICAO shrndard atmosphere.

The operatmg speed envelope of the tanker :u r cralt 18 shown tn f1g\o-e 1 l·37 . Data are presented for both drogue extended and d rogue r etr acted config\lta­tions as a function of gross weight.

SAMPLE PROBLEM

Tanker S peed En velope

(For Cigure 11-37)

(A) Pressure al titude 20, 000 Cl

(B) Gross weight hose and drogue extended , 24 , 000 lb

(C) Minin1t1 m refueling .M;tch number 0. 505

(0) Maximum rducllng calibrated airspeed 300 kn

(E)

(F)

(G)

O'IOCU( ffUMCTCO

- - - O.flOCUE EXTCHOtO

Maximt1m refoehng Mach number

Gr oss weighl hose and drogue r·etracted

Max imu m !\'l a.ch number

'"Al·l82

0. 65

24, 000 lb

0. 86

11-71

I

Section XI Pa.rt 6

E ...

50

NAVA!R 01-'10AVM-l

TANKER SPEED ENVELOPE TANKER CONFIGURATION

1-300 GALLON REFUELING STORE PLUS 2-300 GALLON TANKS 5 PYLONS AND GUNS

MODEL1 A·4M ENGINE: J52-P-408

---- DROGUE RETRACTED - - - - DROGUE EXTENDED

DATA A S O F: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

40 WITH DROGUE EXTENDED, RECOMMENDED LIMITS ARE: M AXIMUM - 300 KCAS OR M =0.8

MINIMUM - MAXIMUM ENDURANCE SPEED

~ 30 OR 200 KCAS, WHICHEVER IS GREATER.

10

0 0 ,2 .4 .6 ,8 1.0

MACH NUMBER

Figw:e 11- 37. Tanker Speed Envelope 11-72

FAl - 186

NAVA!R Oi - 40AVM· I Section X1 !>art 6

SAMPLE TANKER FUEL AVAILABLE FOR TRANSFER

~----····-··--···· ® . ! i i i I i l !0

I TAN«RFua AVAILABLEFOR TRANSFER

I The tanker fuel a.vaUable for t,ransfer ts shown :t.S a function of rndlcs ln fli;ure 11 ·38 !or operallon with J P-4 or J P-5 fuel. The•e data a r e pr e•ented, asstiming standard buddy ... tan.ke_r re.se rves cons1stmg or fue1 for 20 mlntJtos of maxln1u111 cndurnncc at sea level plus 5 pcreCllt or all fuel not 1rans!crrcd. In addition , a fuel :lllowance for rendezvous and hook-up has been added. This allowance consists or fuel ror S minutes at speed for ma.ximtJm endurance, with hose and dr<>1,'\le extended. at 30, 000 feet pressure altltud•.

Al r eiuehng r:ldil or less Lhan 250 nautical 1nilcs with J P-5 fuel and less than 235 nauiical miles wlth JP-4 fuel, the tanker ts w1able to consume al l of the 320 g;iltons of non-transferable fuel. Therefore, ii refoeUng h;: ;1r:1 •omplii::h~ :lf M\d\i lPs;A 1ha.n thOJ;;.t?

I noted :i.nd :Ill tht avaUable rue! ls transferred, the tnnker will return to b3Se with :rn excess or reserve fuel.

SAMPLE PROBLEM

Tanker Fuel Available for T ran•fer

( For Clg\lre 11 -38J

(AJ Relucling radius

(BJ J P-5 Cuel line .

(CJ Fuel available for transfer .

TANKER FUEL TRANS FER TIME

400 NM!

3840 lb

'l'he relation.ship of fuel tra.nsfei·J·ed to receiver ver sus elaJ)SCd time ls presented in figure lJ -39. The flow rale to tht receiver ::u rcraft is 180 gaJJons per minute. Alter 2. 85 nuuutes, r efueling Is tempo­ra r ily d iscontinued 10 a llow the rclucllntt store to rm rrom lhe external fuel t:lnkS.

The max1mun\ arnoulll or ru~ that can be transferred to the receiver during a continuous refueling opera· Uon ts limited to 513 gallons. The 1unumg factor is the external transfer rate of Utnker fuel from the exte rnaJ fuel t:tnks and wing tru\ks to the z·efueling store. II mor e than 513 gnllons Is to be transferred to the receiver, refueling must be dHsoonhnued lO aUow the refueling stor e to be replenished from the tanker internal fuel. The cunc dcJay u; dependent upon the amount or additional !uel 10 be trans!errcd.

SAMPLE PROBLEM

Tanker Fuel Transfer Time

( For flg\l r e ll-39)

(A) File! transferred to receiver (.fl'-5) •

(Dl J P-5 fuel uow llne

(C) Elapsed tlnie

4500 lb

4. 87 min

11-73

I 11

I

Section XI Pa.rt 6

NAVAIR 01-<lOAVM- l

TANKER FUEL AVAILABLE FOR TRANSFER 1•300 GALLON REFUELING STORE PLUS 2·300 GALLON TAN KS

5 PYLONS, GUNS AND AMMO

MODEL: A-4M ENGINE: JS2-P-408

DATE: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

8

7

Cl 6 z :::> 0 ...

... ... ~ 2

0

11- 74

0 100

TAKCOFF WEIGHT = 24,500 POUNDS

200 300 400

TOTAL FUEL ON BOARD

Jp. 4 Jp.5

500

GALLONS 1701 1626

600

REFUELING RADIUS - NAUTICAL MILES

Figure 11-38. Tn.nker Fuel Available For Transfer

POUNDS 11,054 11 ,054

700 800

FAl -1 87

7000

6000

5000

4000

3000

2000

1000

NAVAIR Ol-40AVM-1

TANKER FUEL TRANSFER TIME TANKER CONFIGURATION

Section XI Part 6

MODEL: A-4M ENGINE, JS2-P-408

DATA AS OF: 1 5 OCTOBER 1971 DATA BASIS, ESTIMATED

4 6 8 10

ELAPSED TIME - MINUTES FAl-188

Figure 11-39. Tanker Fuel Transfer Time 11-75

Section XI Part 6

NAVA.IR 01-40AVM-1

I

(D) Polnl where refueling ls resumed .....

:E) Poinl where re(lleli.ng is temporu r ily dis~ontinued

4. 04 min

2. 85 min

SAMPLE TANKER FUEL TRANSFER TIME

i I

:

! ! : :©

I . l : ! :

' ' : I '@;©

! FUEL CONSUMPTION OF TANKER DURING

I AIR REFUELING

The tanker fuel consumption wllh the hoc>e and drogue extended is pre8ented h1 flgure ll-40 for two pres .. sure altitudes for speeds throughout tho night

u Cn\1ClOJ)C.

11-?6

SAMPLE PROBLEM

Fuel Consumption of Tanker During Air Refueling

( F"or figure 11-40)

(A)

(B)

(C)

(D)

Rerueling speed 250 KCAS

Cross weight 20. 000 lb

Fuel now - 20. 000 ft 2860 lb/ hr

Fuel !low - 30. 000 Cl 3020 lb/ hr

SAMPLE TANKER FUEL CONSUMPTION DURING AIR REFUELING

NAVAIR Ol-40AVM- 1

FUEL CONSUMPTION OF TANKER DURING AIR REFUELING 1- 300 GALLON REFUELING STORE PLUS 2-300 GALLON TANKS

S PYLONS, GUNS AND AMMO

MODEL: A-4M ENGINE: J52-P-40B

DATA AS Of: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

sooo

~ 4000 0 ~ "' "' z ::> ~ 3000

I ~ 0 it

.. ::> 0 :z: ....

1000 200

4000

~ 3000 ::>

~ I ~ ~ 2000

~ w ::> ...

1000 200

GROSS WEIGHT - 1000 POUNDS

24

I

I PRESSURE ALTITUDE = 30,000 FEET

I I I

220 240 t 260 2BO

REFUELING SPEED - KNOTS CALIBRATED AIRSPEED

GROSS WEIGHT - 1000 POUNDS

24

I I

I PRESSURE AtlTUDE : 20,000 FEET

120 240 260 280

REFUELING SPEED - KNOTS CALIBRATED AIRSPEED

300

300

Section XI Pai:t G

FAl-189

Figure 11-40. Fuel Consumption of Tanker During Air Refueling 11-77/(11-78 blank)

MAXIMUM RANGE DESCENT

NAVAffi 0 1·40AVM·I

PART 7

DESCENT

Gr.ph1cal data orr prostnird tn figures 11 ·4 I 1hrough 11 .. 43 for maximum r:-m~f.' d~sc«nt using idle thru"l Md with speedbrakes closed. Recommended m:u<I · mum ro.ngc descent s1>ecd. Cucl consumed. dlstnnce <·overed. and el3J>Sed ttme from ruiy des•red ;1.Jtttude to S~Hl ltl'vC'1 :'lr() prcsenfl"d :1$ rt function of g ro.!:iS wci~ht and di·ag lndc.. All data Is based on an ICAO ot .u1,l;1rJ ,tt 111u~v11t'Tt!'.

ThP method or 11z·e1H~:nting dabl ror foel, distance, and tim(" is 1df'nl1r:il. ThArrforP, only on,. sample prob· lcm Is shown.

SAMPLE PROBLEM

Descent Fue l

(For figure 11-41)

(A) Initial gross weight .•• . •. . • • •.. 14. 000 lb

(B) Cru1Sc alliludc 35. 000 It

(C) Drag Index 0

SAMPLE DESCENT FUEL

Note

Section Xl Parl 7

(0) Fuel required from crunile :ilt ltudc to sr:• level . . . . . . . . . . . . 112 lb

From figure 11-42. descent S JlCCd Is 200 KCAS.

Section XI Pat·t 7

"' 0 z 22 :> 0 ... ~ 20

... :r 18 C) .. :c ::: 16 0

"' C)

MODEL1 A · 4M ENGINE: J52·P·408

12 .

150

125

"' 0 100

z :>

ii! 75 I

Ml ~ 50

25

0

11-80

NAVAIR 01-40AV111-l

DESCENT FUEL IDLE THRUST

GEA• UP FLAPS UP

SPEED8RAKES RETRACTED DATA AS OF1 1 DECEMBER 1970 DATA BASIS: ESTIMATED

FAl-127

Figure ll-41. Descent Fuel

26

24

"' 0 z 22 :> 0 ... 8 20

... :r 18 2 i "' "'

16 0 .. C)

14

12

120

"' ~ 100 i ... < v 80 ;: :> < z I 60 ...

v z < .. "' 40 0

20

0

NAVAIR 01-40AVM-l

IDLE THRUST DESCENT DISTANCE GEAR UP FLAPS UP SPEED8RAKES RETRACTED

MODEL: A·4M ENGINE: J52-P-408

DRAG INDEX

0 100 200

12

185 175 165

DATA AS Of: 1 DECEMBER 1970 DATA BASIS: ESTIMATED

OESCENT SPEED SCHEDULE - KCAS

GROSS WEIGHT- 1000 POUNDS

14 16 18 20 22 24 26

200 215 225 240 250 260 270 185 200 210 220 230 240 250 180 190 200 210 220 230 240

Figure 11-42. Descent Distance

Section XI Part 7

fA1·128- A

11-81

Section XI Part 7

"' 0

26

24

!i 22

~

8 20

,_ x 18 ~

i ~ 16

2 ~

14

12

25

20

~ i 15 ~ I i 10 ;::::

0

11- 82

MODEL: A·4M ENGINE: J52-P-408

NA VAIR 01-40AVM-1

DESCENT TIME IDLE TH RUST

GEAR UP FLAPS UP

SPEEDBRAKES RETRACTED

DATA AS Of : 1 DECEMBER. 1970 DATA BASIS: ESTIMATED

FAl-129-A

Figure 11-43 . Descent Time

NAVAU< 01-40AVM-1 Section XI P-ttrl 8

PART 8

LANDING

~ LANDING

ApJ)rollch spocds, stall speech;, :tnd corrcspooding angle-of-nttack units are presented few the l•tndlng configuraUons in figure 11-44. These data aru pre­sented (or an aircraft with gear down and spccd­brakcs open, uslng thrust reqmred to m~inta:.n a 4-dc~rec ~Ude slo~c. IC an B!ll<IC-o!-attack indication o! 18 u1tlts dots not produce the lndlcatcd airspeed as determmed !ro:n !igure 11-44 at the flap settlng used tor npproach, ri?check the confiKu raLlon. If the approiirlatc conltguratlon Is established. distegard the angle-of-attack lndlcaLor and make the approach at the indicated ttlrspeed from figure Jl-44. I SAM .. EPROBIEM

I Approach Speed

(For figure 11- 44)

(A) Gross woi~ht ... • . . ... • .. , • . 14, 000 lb

(B) Stall 8peecl (f'ull fi:tps). . • . • • . . . 105. 4 KIAS Ani:lc o! attack • . . • . . . . • . . . . 25. 8 units

I (C) A1lptoach speed (Full !lap•) ...... 126 KIAS

I Ancic o! attack • • . . . . . 18 units

Landlstg g round.-r o ll dlsboccs a re fl ref>t>n~d in !igures ll-45 and Jl- •16. Fl~urc 11-45 presents g.rc>und·1·oll cti~l:'lntelS wilhoul drag chute ll.l\d fi.p;­urt.> 11-46 presents ground·roU dlst:ances using the dJ't'lg ChuLc. Dntn f1ro prO\•id~d for lh.ree runway

SAMPLE APPROACH SPEED

' I i !@

FAl-190

conditions: dry . wet, :and snow and lee. All dts­t:tnces are b:ased on ;ln :lircrafl with !:i(>eedbr:tkes and spoilers fully extended, !laps as set !or ap­proachi appr oach speed.s ~Hi determlned from figure 11-44. m:i.~lmum braking eUort wJthout sklddlng the tires, and the throttle set at idle throughout the ground-roll.

To ut'le the l;\ndlng distance ch.arts . the temperature, pr~ssure altitude, gros• weight, !tap dc!lcctlon. he:utwind, nnd ruoway gr:.1d1ent must be known. The distance to clear a 50-root obstarlc 1~ me:t~"Ured hOr i1_,onl,.alJ}r [rom the 50• (00l ObSt...'kcJI" IO lhe end O( the KJ'Ound roll and is determined by addll~ 715 £eel to the gro~md-ro11 distance. nssuming a st.and.1rd 4-degree glide slop•.

11-83

!

Section XI Part8

NAVAIR Ol-40AVM- 1

APPROACH SPEED GEAR DOWN - SPEED8RAKES OPEN

THRUST REQUIRED TO MAINTAIN 4 • GLIDE SLOPE

MODEl 1 A-4~ ENGINE: J52-P-408

DATA AS Of: IS OCTOBER 1971 DATA BASIS: ESTIMATED

"' 0 z " I s ... ... "' "' c 0 ... ... < ... i5 ~

160

ISO

140

130

!>

120 .j

!.-..I<

I->-110

t ],,

...! ·t µ. ........

100

~ 90 10

11-84

µ w H-

~ ~

~ !>~

.. rT

~ .

-~

·-br' A:'.

. r. ~ S; t:." t- ~ ~

I+ H t l- -~~

~ t-i ~ .... H- ~ Ji .;

\;-"~ J.,i,.. j ~ 1n 1-1

~ .lj l ~ ;. 1 t b'. ~ ~ +1

H-+- w. ~

' 1~ 4 -- - -"- :+._J f-1-? + ~f-t '

. -~ h-< . ri!t'>..i.. ·-·-

~k~ ~ .H r-t + t+ ~+· ·-+++ 11 12 13 14 15 16

GROSS WEIGHT- 1000 POUNDS

FAl-192

Figure 11-44. Approach Speed

NAVAffi 01- 40AVM-1

LANDING DISTANCE HARD SURFACE RUNWAY

DRY SPEEDUAKES AND SPOILERS OPEN

RCR = 23 NO DRAG CHUTE

Section XI Part 8

MODEL: A•4M ENGINE: J52-P-408

DATA AS Of: ts OCTOBER 1971 DATA BASIS: CONTRACTOR FLIGHT TEST

-!20 -10 0 10 20 30 40

APPROACH FLAP HALF

DEFLECTION

HEADWIND -KNOTS

RUNWAY GRADIENT - PERCENT

SLOPE

- 2

-+-0

.,.

+2 tJ..1 0

UP

w .. 111 , -t'· ' ·+ Wl ~ .l r i$l i~ ri i!kt:! '

Q;;) If .j • I l H

~~ »1. ' I J d ...,, -r-,.,.j - " 08 HJ 'r' t ~' i;;.; 7 + --+; f ''-' l'. >-+ ...

f+i- tTt •I

"":!I .... ' !+

t:.t. w 1'1~

ry ~p f ' -~ ;\. ...

2 4 6

LANDING GROUND ROLL DISTANCE - 1000 FEET

Figure ll-45. Landing Distance - No Drag Chute (Sheet 1)

.

10

FAl-193

u-iss

Section XI :Part 8

NAVAIR 01- 40AVM-l

LANDING DISTANCE HARD SURFACE RUNWAY

WET SPEEOBRAKES ANO SPOILERS OPEN

RCR: 15 NO DRAG CHUTE

MODEL: A-4M ENGINE: J52-P-408

DATA AS Of: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

-20 -10 0 10 20 30 40

TEMPERATURE - •c APPROACH

FLAP DEFLECTION

0

10 t HEADWIND 20 -KNOTS

30

40

- 2 RUNWAY GRADIENT

0 - PERCENT SLOPE

+2 L 0

BASELINE

2 4 6 10

LANDING GROUND ROLL DISTANCC-1000 FEET FA1 · 194

Figure 11-45. Landing Distance - No Drag Chute (Sheet 2) 11- 86

NAVAIR 01-'10AVM-l

LANDING DISTANCE HARO SURFACE RUNWAY

SNOW ANO ICE SPEEDBRAKES AND SPOILERS OPEN

RCR : 9 NO DRAG CHUTE

Section X1 Part 8

MODEL: A-4M ENGINE: J52-P-408

DATA AS OF: 1 S OCTOBER 1971 DATA BASIS: ESTIMATED

i :EH:;fH H t

rti\lJ ' "fl l'I

J#.' I it .., fi:J~ •'/, 11'/'-f! 1 t- j -

~ -I -V; ~ 'i-1'-d() ... "1 .... -· t:t ~-W ....

Vi ~

' - 20 - 10 0 10 20 30 40

TEMPERATURE - ° C

0

10

HEADWIND 20 -KNOTS

30

40

-2

RUNWAY GRADIENT

0 - PERCENT SLOPE

LANDING GROUND ROLL DISTANCE - 1000 FEET FAJ.195

Figure 11- 45. Landini; Distance - No Drag Chute (Sheet 3) 11-87

Section :ll.'I Part 8

NAVAJR 01-40AV.M-1

LANDING DISTANCE HARD SURFACE RUNWAY

ORY SPEEOBRAKES ANO SPOILERS OPEN

RCR = 23 WITH DRAG CHUTE

MODEL: A-4M ENGINE: JS2-P-408

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: CONTRACTOR FLIGHT TEST

-20 -10 0 10 20 30 40

TEMPERATURE - °C

APPROACH FLAP HALF

DEFLECTION

UP

0

L1 10 ...

HEADWIND 20 -KNOTS

30

40

-2

RUNWAY GRADIENT 0 - P!RCENT

Li. SLOPE +2 ...

0

LANDING GROUND ROLL DISTANCE - 1000 FEET FAl - 196

Figure 11- 46. Landing Distance - With Urag Chute (Sheet 1) 11-88

MODU: A-4M ENGINE: J52-P-408

NAVAIR 01-40AVM-1

LANDING DISTANCE HARO SURFACE RUNWA Y

W ET SPEEOBRAKES ANO SPOILERS OPEN

RCR = 15 WITH DRAG CHUTE DATA AS OF: 15 OCTOBER

DATA BASIS: ESTIMATED

-20 -10 0 10 20 30 40

TEMPERATURE - °C

APPROACH FLAP HALF

DEFLECTION

10

HEADWIND -KNOTS

20

30

40

- 2 RUNWAY GRADIENT 0 - PERCENT

SLOPE

LANDING GROUND ROLL DISTANCE - 1000 FEET

Figure ll-46. Landing Distance - With Drag Chute (Sheet 2)

Section XI Part s

1971

FAl-197

11-89

I

SecUon XI Part 8

NAVAIR Ol - 40AVM-1

LANDING DISTANCE HARD SURFACE RUNWAY

SNOW AND ICE SPEEDBR.AKES AND SPOILERS OPEN

RCR = 9 WITH DRAG CHUTE

MODEL: A·4M ENGINE: JS2- P-408

DATA AS OF: 15 OCTOBER 1971 DATA BASIS: ESTIMATED

-20 -10 0 10 20 30 40

11-90

TEMPERATURE - •c APPROACH

FLAP DEFLECTION

HEADWIND -KNOTS

RUNWAY GRADIENT

- PERCENT SLOPE

- 2 l

0 l

+2 0 2 3 4 5

LANDING GROUND ROLL DISTANCE - 1000 FEET

Figure 11-46. Landing Distance - With Drag Chute (Sheet 3)

6

FAl-198

NAVAIR 0 1- 40AVM - l Sectlnn Xl Part 8

SAMPLE PROBlEM (A) Outside a ir tempe ratur e

landing Distance

(For ligure 11·45, sheet 1 and figure l 1·46, !heel l ) (B) Runway pressure altitude . . 2000 It

Runway Condition : Wel

SAMPLE LANDING DISTANCE (C) Landing gr oss welght. . . . . . . . 14 , 000 th

(D) Approach flap deflection . . . . . . Hall

(E) Headwind . • • . . . 20 kn

C•') Runway g radient • . . . . • . . . . . -I percelll

(G) Ground l'Oll distance:

No drag chute .•... • . ...• . • 3200 fl

With drag chute . . . ... . .•.. 2020 It

11-91/ (11-92 b lank)

NAVAIR Ol - 40t\VM - I St·dmn XI Part 9

PART 9

COMBAT PERFORMANCE

COMBAT PERFORMANCE

Thi s par·t cont.:lins Lhc ,wrCornl311\'0 cha1·h, 3$iSOCJ3tcd wlth th(' combat phase of the mission. Turnln.: r:.tdtus, maneuvcrah hty. ma:dntum Ma('h nunt':>er. nnd nid1l3rv fuel flo·.v 0. 10 im.·luded.

TURNING RADIUS

Th<" 1,1r11ini: r:td1m; rnmograph, fiq\tre 11-47. pre­sent~ dat.3 for ~leadl' &tak level lul'n8 :L"l. a funct1un <1f u•uc- alr~pccd. no1·m:il load facLor. bank nnit1l', dlstonco u·~vole<l. aid heading change. When used m t·nnJunrthm wHh the ln:td hu:lnr limHntlmu. of tlw maneuverability ch...\1·ts. tlgure 11-48. tile i.'erodyn­a·nlc. cn~lnc. and s·_ructural charactcrlstic.s or the :urc1•aJt :.tre Laken 1nto :t~counl.

Note

At normal lO\\ llvol a irspeeds a rout-th 1>lan­nl.ng- ald tor turntni: ri'dJus Is the use of a drnm on :..tn ONC (1:1 , 000, 000) ur 3 qu:t rt~r on a PC (1:500. JOO).

SAMPLE PROBLEM

Turning Radius

(Fm• fl~ul"O IJ-47)

Prom l\1:111eu\1ernbl1!ty Sample Problem J (Flg:· Ul"I' 11--18)

M.tch Numher 0. 75

Normal Lo~d F:tc tor . . . . . . • . 3. 84sr

(A) Normal Load F>etor • . . • . . . 3. 84~ (Bank An~le •..•• 74. 6 Degrees)

(n)

(C)

SAMPLE TURNING RADIUS

@ -__

- ..... _ _ ©

------ @

U:U TUU LOtD UH l.llSP£U UDIVS JACTOI AKUl

----+-------i

True 1\lrspcod 49& KTAS

Tu rnmg ff:idtuK 6000 fl

(D) Hendinit change •....•..•• . ... 90 dc~rees

(E) DiMoncc Tr•"olcd In Turn 9200 h

MANEUVERABILITY

Low·althudo mnnou,•orabilhy charactcrlslic> of the A- 4M ain·r3ft are shown ln rl~'Urc 11-"8. These data pro\'idti a means ot dctcrmtninJt elthrr th(\ maximum lo:\d f::ti•fl•l' !'ltl:\iunbt.1 nl ti "fW'c•ifiNI M:lrl1 1tumlwr (sample 1>ro'blcm 1) or the nmxlmu111 (and 111 tot mum) M3rh number fl'u- :t predrte-rmln~d load r:trtor re· <1oirement (1:>.·un111e problem 2). The8t.! d:•la. :tr-f• pre­i,ented ns tt Cunctlon of altltude. normal lvad factor

11-93

I

Section XI Part 9

600

550

soo

450

400

3SO

300

2SO

200 AIRSPEED IKTASI

ISO 30

20 100

50 10

s 4 3

2 10

400 300 200

100

so

so

10

NAVAlR Ol-40AVM-l

TURNING RADIUS

s 4

3

2

1.0

.S

30

20

10

s 4

3

.2

.1

TURN RADIUS 11000 FEET -

NAUTICAL MILESI

---------1.Q,..

5 111--- s 1.0

.s .s

.1 .s

TURN RADIUS 11000 fEET -

NAUTICAL MILESI

.5 .1

.2

DISTANCE TRAVELED IN TURN

11000 FEET­NAUTICAL MILESI

1.02

I.OS

1.10

\ ,S

4

s 6 7

NORMAL LOAD FACTOR

------

10

20

30

40

50

60

70

80

8ANK ANGLE IDEGREESI 180

ISO

100 90 80

60

50

40

30

20 HEADING CHANGE

IDEGREESI

FAl - 134

Figure 11-47. Turning Radius 11- 94

... % I)

~

90

80

.,. so () .. I)

x

:5 40 .. 0 t; ~ 0 <( 30 g

~ "' ~ 20

FLAPS UP

MODEL: A · 4M ENGINE: JS2· P·408

0 0.2 0.3

NAVAlR 01- 40AVM-1 Section XI Part 9

0.4

MANEUVERABILITY MILITARY THRUST

SEA LEVEL STANDARD DAY

GEAR UP

DATA AS OF: 1 D£CEM8ER 1970 DATA BASIS: ESTIMATED

....;.

0.5 0 .6

MACH NUM8Elt

0 .7 o.a 0 .9

FA1·135

Figure 11- 48. Maneuverability (Sheet 1) 11-95

I

Section XI Part 9

FLAPS UP

M ODEL: A-4M ENGINE: J52-P-408

.,. () "' I)

x ~ 40

0.2 0.3

11-96

0.4

NAVAIR 01-40AVM-1

MANEUVERABILITY MILITARY THRUST

10,000 FEET - STANDARD DAY GEAR UP

DATA AS OF: 1 OECEM8ER 1970 DATA BASIS: ESTIMATED

0.5 0 .6 0.7 0.8 0.9

MACH NUMBER

fAl-136

Figure 11-48. fllaneuvel·ability (Sleet 2)

NAVAIR 01-40AVM-I Section XI Part 9

SAMPLE MANEUVERABILITY

times gros;s wcighl, Mach nuinbcr, aod drag ind.ex for zero longitudinal accelcratlon. SUpcrlmposcd on the grnphs are line.is $hOwing maximum h!l, buffel onwset, and structural limits. All data presented are based oo the Crlginc dcvclopiitg milita1·y thrust.

SAMPLE PROBLEM 1

Maneuverability

(For figure 11-48, sheet I)

Altitude . . . • . • . • . . • . . . . . . . . . Se:.. level

Gross weight 18,000 lb

(A) Mach number o. i5

(D) Drag index . . . . . . . . . . . . . . . . . . 50

(CJ Normal load factor x gross weight . . 69. 000 lb

Gross welght. . . . . . . . . . . . . . • . • 181 000 lb

Normal lo:id fact.Or at zero longitudinal acceleration . . . . • • • . . 3. 84g

SAMPLE PROBLEM 2

Maneuverability

(For figure 11 -48, sheet I)

Altitude Sea lcveJ

Gross weight . . . . . . . . . . . . . . . . 20. 000 lb

No rmal load factor required 3.0g

(DJ Normal toad factor x gross weight .....•. 60, 000 lb

(E) Drag index . , . . . . . . . . . • . . • . . . 100

(F) Mirl imum Mach number at 3.0g .............. ...... 0.434

(G) Maximum Mach number at 3.0g . . .. . •.............. 0. 731

SAMPLE MAXIMUM MACH NUMBER

11-97

I

Scctlon Xt P3rt 9

NAVMfl 01-40AV~l-I

SAMPLE MILITARY FUEL FLOW

MAXIMUM MACH NUMBER

Level rl11.thl mnxrnlum '.\•larh numh~r. :tl milil~4 rv thrust. is shown ln figure 11-49, o.s a (unction Or

11-98

dr:.1! mdex :rnd p-oss wcli::ht at altitudes of .bea le''<•I and 10, 000 feel. Military thrust fuel flow is pr('­scmcd lt\ H,Hurc J 1-50 tu;. n fun('tion of pressure altitude and Mach number.

SAMPLE PROBLEM

Maximum Mo<h Number

(For fit!"rc 11-49)

(AJ Oraii Index .•••• , .• , •. , . • . . . . 60

(B) Gro"" wei~ht al sea level ..•. , •.. 18. 000 lb

(CJ 0. 833

SAMPLE PROBLEM

Military Fuel Flow

(For f!~ro 11 ·50)

Prrn1surc altitude 10.000 It (A)

(13)

(C)

\laci1 nurube r ..... _ . _ • . . . . . • 0. 90

Fuol Clow .. , ••..•. , • . • . • . J 56 lb mln

MODEL: A·4M ENGINE: J52-P-408

NAVAIR 01- <lOAVM-l

MAXIMUM MACH NUMBER MILITARY THRUST

ICAO STANDARD ATMOSPHERE

DATA AS OF: 1 DECEMBER 1970 DATA BASIS: ESTIMATED

1.0 -,..,...,...,...

f. 1 -

"' ... "' .9

" :> z :r v ~

" ... il .8 ..

,1

.. ... .. " :>

.9

z :z; v ~

" ... :> .8 .. ..

0

i.- ~tEVEJ. I ~ rt

....., I ~ROSS WEIGHl 1000 POUNDS 1-1-.;._"-1-.i...;.......U

,_......t+r+H-rtiH-:-H--t+++i t-'12t

40 80 120 160 200

40 80 120 160 200

DRAG INDEX

Figm·e 11-19. Maximum Mach Number

Section XI Part 9

FAl-13'

11-99

I

Section XI P8l·t 9

11-100

MODIL: A·4M ENGINE: J52-P-408

NAVAIR Ol-40AVM-l

MILITARY FUEL FLOW ICAO STANDARD ATMOSPHERE

DATA AS OF: 1 DECEMBER 1970 DATA BASIS: ESTIMATED

100 120 140' 160 180

FUEL FLOW - POUNDS PER MINUTE FAl-1 38

F'igure 11-50. Military Fuel Flow

l'AVAIR 01-40AVM-I Section XI Port 10

PART 10

MISSION PLANNING

MISSION PLAN NING

Optin1unt use or 1he alrcr3.!t to obtain m:iximum performartce 'lt a mmjmum rate of fuel consumption requires careful pr eflight planning for the nHsslon.

I One of lhe mosL lmp0rlant phasei; of n11ss1on planning is the dctermln.a1ion or the m::&.ximum radius or action from the field which will allow return with a n adc-1 quate fuel rC11erve.

! To rind the mal<ln1un1 radius. a combat plan must be formulated in advance, and a loiter altitude and dis­tance must be e8ta.bl 1shed before the combat phase of the mission is bcguo. Fuel consumption is high dur­ln~ combat n10nc,vers and any delay In beglirning the combat acuon will shorten the con1bat time. or seri­ously reduce the amount of planne-d fuel r eser ve.

The ro11owing 8a.rnpte problem is an exercise ln the uso of the pcrfor:naorc rharts contained in Parts 1 through 9. The example is not Intended to r eflect a.n actual m iss1on. The sample problem must rates. through a grJ.phical solution, how the porformanc~ charts can be rnt~g1·ated tu (O rm a complete mission Cllght plai1. The steps used to develop such a plo\ a re shown with the problem.

I SAMPLE PROB~M

I TakcoLC and proceed un cour-sc al 25. 000 fotlt allttude al maximum ran~c ~tach number. dcs~~nd to 5000 loet almudo: hold on suuton awaiting lnstruc­Uona I rum ground observers then :lttnrk the target

I v:Uh two du.sto1-s of SxM K 91 LOCP lxu\lbi:i alo1ti; with two single MK 81 LDGP bombs. RetuJ"o to thc- held al maximum ran0e cruise oltitude with 800 pounds o! r esen·c ru..-L f\1llowinf: 15 a plan view.

SAMPLE Pl.AN VIEW

~

~ FIELD

Assumptio ns and Comments

TARGET

FAl-199

Assume zero wlnd and ICAO standard day rond1t1on!'S.

2. Assume the gun ammunitlon I~ 1101 rtrcd during lhe n11ss1on. ·

3. Assuuw • combat allow:uwe of S mtnutcs at l mUita1·y lhrusl lU drop the bombti al cJw Larg-~t. ~

11-101

I

Sec:;llon Xl Pai1 10

NAVAIR 0 1-40AVM-I

I The Sample Mission Planning Problem Summary

!ij solution of the problem is introduced at this J>Oilll so

•he pilot can see 1he oom1>lete graph!<' picture before the :lch.Hl.l soluhon is broken imo parts.

SAMPLE MI SSION PLANNING PR08l ( M

14eo. ,,,n,.

CllMS TO 2-5,000 net _ l

Df.SClNO'l'fO ~l()AT

~'JO?Ftl1

r Cr&AT T

CLIM& TO OPTIMUM AlTITU-0(

• ' C"U*Sl IA()( AT OflTIMUMA\.llTUO(

' APP!t04CH "-110 l oott:NO TO su. uvn l.AllONCltlSUV\

100 700 )00 400 OISTANCC · AIR NAUTICAlMllfS r1,1.200

The p•·oblem is solved by 1>lotting fuel remaining versus air distance. Gross weight is also super ..

I Imposed on the vcrtic:\1 scale.

The Urst s tep ts to derive gross weight and dtag index values as shown. The mlsslon problem is then

_ solved ill ii1cremental step8, working from takeoU

I through descent and working b:...ckward Crom landing to combat.

Start solving the mission requirements by working backward from the landing reserves. The solution follows.

ll-102

Gross Weight and Drag Index

(From figur e 11-1 and NAVAl!l 01·40AV-IT)

Drag ltPms Jndex

Zero fuel, zero payload 0

Two 20mm guns and ammo

Two station 75 wing pylons 12

•rwo i;tation 113. 75 wing pylOl\S 11

Two .\ '1t-;R·7 on station 75 46

One 300-gallon bobtail fuel 1:rnk oo cc1lterli111~ station 15

Two 5x.~1K 81 LDGP bombs 28

Two lx!\lK 81 LOGP bombs on st3.t ion l 13. 75

fatc tnal fuel (800 gallons JP-5)

External fuel (300 gallons JP- 5)

Ta.keolf Tol«ls

Drop 300-gallon tank

Total

Drop bombs

Total

Fuel used (inicrnol)

Fuel used (external)

Total (zero ruel weight)

126

-15

Ill

-32

79

79

\V('Jt~ht (pound<)

11. 427

628

140

128

446

183

2GOO

520

5440

2040

23, 552

- 183

-3120

. 5440

-2010

12, 769

Approach a nd l a nding Reserve Allowances

!

'T'he landing r eserve js assumed to be 800 pounds I which will permit sea level landing patte rn operation for 15 to 20 minutes . This poinl is plotted as showo 0 1\ the Sample Cruise Bac.k1 Descent. and Laoding Reserve plot at 800 pounds of fuel remaining and zet'O n.auLical miles distanc;e.

NAVAIR 0J-40AVM-1 Section Xl P:tn 10

I Descent from Optimum Cruise Altitude lo B Sea level

Time, iuel, and d\stance for descen1 can bl' deter· mined from the desc~nl charts (hgures 11-4 1 1hrl)U~h 11-43). The drag Index !or this con!iguratio11 Is 79. Assume ;hat the weight at the beginning or t he letdown is equal to the gross weight with rese rve fuel ( 12, 769 lb · 80~ lb ~ 13, 569 lb). The o!)timurn c ruise altitude !or this weight and drag index Is read Crom figure I l-20

Distance Tln>e (nautical

Initial Weight

(pounds)

Optil';\um Cnalsc Altitude (le<!) (minutes) nilles)

F'uel (1x1<1 nds)

13, 569 38. 700 15 64 110

'l'hcse values are ploucd as shown on the Sample Cruis~ Back, Ocscc11l , and Landing Rcsen•c plot at fuel r ematntng ol 910 pounds (800 lb • 110 ib • ~l O lb) and 64 nautical miles dJ.s tance.

Re tu rn al Optimum Cruise Altitude

T he opclmun\ croise ahttudc fuel requiremcnti:; can be dete rmined from hgur·es 11-27 and 11 · 28. The d rag index Is 79 and Lhe weight at end of cruise ls 13, 6i9 JJOUnds (12. 769 ib • 800 lb • 110 lb = 13, 679 lb). Assume arbitrary cr uise fuel increments and con­struct t he r etum fuel -disLance hne as shown 0 1\ the Sample Cruise Back . Descent. and Landing Reserve ploL

Fuel A·1e r:lge Increment Wei~hl (pounds) (pounds)

500 13 , 929

500 11. 429

500 Ji, 929

Nautical Miles per Pound (lf F\Jel

0. 224

0. 216

o. 200

Optimum Cruise Altitude 01;Jt1mum Cruise

(feet) Mach Number

38, 200 0. 685

37. 100 0. 685

36. 900 o. 685

01sranee Increment (na.ut ical miles)

112

108

105

These points are pioued as sho"'" on the S.1mplc • Cruise Uackr Descent , ~nd L.anding ll<'srrve plu1 at tj fu~l r emarnini; t1f J4JO, 1910, and 2410 pounds I r especlively (ruel r emaining - rcbCr\'C rucl • descent fuel + crulsc rue:J tn('r<'-mcnt). The COl'rf'.!SJ>onding dlslancc points are 176, 284 1 nnd 389 :ur nauhc:ll rnalC!'S (d1st.anee • descent dlst:rnce i dlstat1te lm·rernent).

SAMPLE CRUISE BACK, DESCENT, ANO LANDIN G ltESUVE F\l(L Qlt0$$ W(fQff1

I llOl.-'\0$ PO~OS

"Off: AJl61lll!AlfV VAt,UlS Of Flll.l C01f$\Uo1£D A&t£1.l5EO THl\"OlttT\I~ C:ltl.llU U'IC.

• 2410 . l~,17'9

2 • 1910 • lA,"19

1410 ... J),f.79 l),,61.

6A 1 Jt. 28A

lOO lOO 300

OISTANCC-AIR NAUTICAL MlltS

Climb to Optimum Cru ise Altitude

,.,, .. ,

The tlmc, fuel , and dis Lance to cJln11> from sea le,·cl to optimum cruise altitude can be dcterml11ed from figures 11·16 th.rough 11-20. Assume two arbitrary injtial climb weights of 15, 000 and 15, 500 pounds aod read the values a.1 79 drag mdex. Conslnact r ight triangle fuel -distance lines as shown on the Sample Combat and Climb to Optimum Cruise Alli · tudc plat beginning at the app ropriate fuel ~n'l3.h1lng \lalues on the r etu rn a1 optunum cruise ::i.llltude linf:" (fuel remaining .. assumed initial c.·Im1h we1gt.l -zer o fu~I weight - fuel LO cJhob).

Ln!Jlal F'uei

I

Weight Fuel (pounds) (pounds)

15, 000 560

15. 500 600

Distance (nautical

miles)

38

39

Time (n\inutes)

5. 9

8.0

Remaining I (pound>I)

l G71

2131

11·103

Section XI Part 10

NAVAJR 01·40AVM·l

w Combat

A Iive--mlnute sea level, maximum speed, combat allowance is assumed to exJ)end the bombs over the target. To per mit a conservative fuel allowance, it is assu1ned thal the bombs have been dropped prior to combat and the drag index 1$ ?9. Since the varla · tion i n maximum speed with g ross weight a t sea level is small assume that the combat wei&ht js that weight which is determined by the lntersecti01\ or the clinlb li1le and the requ ired mission radius (combat weight = zero fuel weight + fuel r emaining at 300 nautic-2.l miles (15, 149 lb = 12, 769 lb + 2380 lb). From fig · ure 11-49 at a weight of 15, J49 pounds and drag index of ?9, maxjmum Mach number - 0. 819. _From !ig: · u r e t 1-50 at sea level and Mach number or 0. 8 19,

I fuel flow .11: 169 pc>unds 1>er minute . Therefore fuel for 5 minutes ls 845 pounds. The combat allowance o f 845 1xmnds 1s addPd to t h" fot>1 " "m'11ining ;111

.

300 nautical nules. Assume that no d istance is cov­ered durlng combat.

SAMPl.E COMBAT ANl.l CUM& TO OPHMUM CRUISE ALTITUDE

. 7480

CllOSSWEIQHT P0\1'10S

2l.SS2

MOT[ CL/ll8 l"IA'.L AMEi OJSfAl>Cf 1$ llf.0TTCOA$ A ltl,HI fltlA..'iQt,[

CLIM8 OISTA..'tCC

C.Jf/'- 1Slf1Al.Clf»8Wt:l(;ll'l

a~v l2is. a.~74 . lltTUtSEGT'°"' o~

' 'V(t, •t:UA.lltlN'-77,1 • U,S.OO • A!llO CltUISE t,IN(

• Z)'JO · U,lA9 • 11'1 • U,000 tl)l l4,'>00

• t(>1) • lA,A~O

212 270)00) 0)69

100 20 )0 400 OIST.\NCE: ·AIR NAUTICAl MIU$ flA\ · 202 I

I. T ax1, T akooff, a n d Acceleration

The h rst po111on of the plot 1s constructed by working W.ckw~rdi:> rrom U\e Jancung reserve. 7he remainder of the plot l~a1l be developed b)' startmg at the taxi · takeoff condition Ta.keoH weight 1s 23, 552 pounds

• with a drag index of 126. Ai;sume a fl\·e-minute ta.xl

11-104

fuel How at J2 pounds per minute , takeoff I accele ~lion allowa1tces of 150 pouods o! fuel used, and no d1staocc covered . Plot this point as shown on the San1plc Takeotr, Climb, Cruise, Dcsct!nt, and Hold on Station plot at 7270 pounds or fuel remaining (7480 lb • 60 lb • 150 lb - 7270 lb) and zero distance cove red.

Climb to 25,000 Feet Cruise Altitude

1'he time, fud, and distance to climb values arc read from figur es Jl ·l8 through ll -20 at a drag index of 126 a1\d an initiaJ weight of 23, 342 pounds (23, 552 ib • 60 lb • 150 lb = 23, 342 lb).

l.nilial Wclght Fuel Distance Time (pound•) (poundc) (NMI} (minut<:3)

23, 342 740 37 6. 0

These \falues are plotted, as shown oo the sample plot , at a Cue! ren1ai11i11g ol 6530 pounds (7480 lb -60 lb • 150 lb = 6530 lb) and a distance ol 37 nautical miles .

Cruise Out at 25,000 Feet Altitude

The initial cruise -out weight is 22, 602 pounds (23, 342 lb • 740 lb = 22, 602 lb). and the drag index ls 126. The fuel r emaining In the 300-ga llon drop tank is 1090 pounds (2040 lb - 60 ib -150 lb - 740 lb • 1090 lb) and will be used duri11& the init ial porti on of the cruise-out leg . Read nautical miles per pound of luel fr om ligures 1 l ·27 and ll -28.

Fuel locreme1u (pounds)

1090

Average Weight

(pounds)

22. 057

Maximum Range Mach

Nuntber

0. 635

NMV Pound or F'ucl

0 .131

Distance Inc r ement

(NM!)

143

Plot these \'alues as shown on the sample plot at a fuel r cmainrng or 5440 pounds (7480 lb - 2040 lb • 5440 lb) and a distance ol 180 nautical miles (37 NM + 143 NM • 180 NM).

At this Point t he external fut~l tank is dropped and the aircrait weight is 21,329 1>0Und• (22,602 lb. I 1090 lb • 183 lb - 21. 329 lb) with a dra~ index of l II (126 - 15 ,.. 111). Assume arbitrary iuel increments . . and cootinue Lo com;tnict the cruise out line.

NAVAIR 01·40AVM·l Section X1 Part 10

Fuel Average Increment Welghl (pounds) (pounds)

500

500

21,079

20, 579

Maxlmum Ra.ngc Mach

Number

o. 635

0.630

NM!/ Pound of f"el

0.137

0. 141

Distance Increment

(NMI)

69

7 1

These values att plotted as shown on the sample plot at fuel r c111ainln;< values ol 4944 pounds (r.44 0 lb· 500 lb= 4940 lb) and 4440 pound• (4940 lb • 500 lb = 4440 lb) with corresponding dista nces of 249 nautical 1111lcs (180 NM • 69 NM • 249 NM) and 320 nautical miles (249 NM • 71 NM = 320 NM).

0PuP.nt tn 5000 F~@'t A.lti.t ude from 25.000 FP.Pt

Altitude

Assume the intUal descerll weight is that weight which ls determined by the intersection ot the crutse · out line and the required mission radius (300 NM). rrom the graph fuel rema.tning at 300 nautical m11e& is 4590 pounds: ther~fore the assumed initial descent weight Is 20, 479 pounds (23, 552 lb - 7480 lb -183 lb• 4590 lb • 20, 479). Re~d time, fuel , and distance to descent fron> figur es 11 - 41 through 11 · 43.

Initial Weight

(pounds)

20. 479

Time (minutes)

G. 7

Distance (NM!)

30

Fuel (pounds)

46

These .. iatues are plotled as shown on the sample plot In lhe following manner. The distance of 30 nautical miles is covered Jn the descent. To :J.rr.ive at the­rcquired mission. r.ulius at 5000 feel, a point is plotted on the eruise·oul hne at 2'10 nautical miles (300 NM - 30 NM • 270 NM) At lhls po1111 read Cue! remaming of 4800 poul'\ds; therefore fuel rcn1aloing at 300 ru>.utlcal miles Is 4754 pounds (4800 lb - 46 lb • 4754 lb). The aircraft has arrived at the required n\lsston radius (300 NM) with a luel ren1ainlng ol 1754 poonds.

Hold on Station al 5000 Feet Altitude Over

Target

The fl.1\al step Ir planning the mission is to determine the loiter time ovallable over the target wllh the remarnmg fuel. At this pol1\t H is adv1sPd that an the varioos parts or th-O problen\ be integnued into a single sun1mary 1>lot as shown :u the bcgl11ning of the probl~nt. Fuol :lVllil:tblc for l<"itcr le then found tO be the fuel remaining at end or descent to 5000 feet, le-Ss the Cue-J rema.ming at sta rt or conibat. Fuel available is 1529 pounds (4754 lb - 3225 lb= 1529 lb).

It Is assumed that the holding cond.ltion is Clown 111 •

race track pattern and the average bank angle ts 15 deg rees. lt is also assumed that the stores are retained throughout the loner.

Average gross weight is 20, 062 p0<1nd• (23, 552 lb·

7480 lb • 3225 lb •~ lb • 20, 062 lb) with a drag

Index of 111. From figures 11 ·35 and 11 ·36 read loiter conditions.

Average Weight

(pounds)

20, 062

Ma.xiroum Endurance

M>eh Number

0.370

Fuel Flow (pounds/hour)

2910

Ho1d Trn\e at 5000 Feet

Altitude (minutes)

31. 5

The mission requi rements can be met, providing that the bold time over the target is restricted to approxi· mately 30 minutes.

SAMPLE TAKEOH, CllMt, c • u1st. oucon, ANO HOLD O N STAHON

• r~os '~.':l'Gtll

. , .. 0 '1,)51

. 1210 . 2'."41 (6.llrilt

MtO · n,•02 · CM\llH W1TH UU:ltllAl,TAhl(

m n llO no no

TAKEOFF AND lANDING DATA CARD

CeM:tin items or tn.keoff t>erformance can be entered 01\ lhe 'rakooH and La.ndini' D:ila C:i1·d fur c~. " 'Cmtnl reference. Entries illustrated on figure 11 f.12 are rrom the sample n\Sssion problem and nm.}' ~c read from Section Xl. Part 2. NormaJ lane.Ung 1lCr· formancc data arc available in Pan 8.

II · 105

I

Section XI Part 10

CRUJSF AT 2-~. 000 J.""T (TA~K OROPPFO)

01-:scE!\T TO 5000 .. ,.

1101.0 AT ~000 FT

CO)llJAT

CUMB TO 01'1'1)1\; M J\(.TllTDE (OPTl'101 IJ,T!Tl'DE

37,500 l'T)

CHL'ISL UAt'K AT 01'1'1Ml")1 Al.:l'l'l't:Dt; (F!:<,\L ALTITL'OF.

3~,5()() F'l')

D~SC>:XTTO $1!;1\ LJ::Vt:l,

.\PPH.0.\CH .-\l\ll

TV l'.\l~

21,329

20, 689

20. 043

l~, 97 ..

11;,t.l!)

13,679

13 . ~69

NAVAlR 01 -40AVM· l

6·10 14 . 2

6 . 1 30

1529 31.S

570 G. 0

900 30. 2 !!>a

110

H~U 1U.0 tiOCt

Clll1fSf: SPF.F.O - KCAS

27 10

l)ESCE!<T SPLED - KCAS I 220

l.OtrnR SPr. P.ll - KCAS n·~~ ~;~w

22:;

MACll :W'IJ3Ell

o. ~ 19

2910

FUEL n.ow LU llH

10, 110

l~T- 10001'1' CLIMB Sl'Ff.0

Kt.:AS OH .MACll

CHl'ISE ~LICH~I t'UtL !'LOW SPEEn / KCAS I Ul 1111

OESCE~'T SPF.ED- KCASI

IW I

1

1 .. \).;l)lNC ltl:;SJ·;nv~

....____ __ f.'igure 11-51. summary of $.'\mple Mis8ion

11-106