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CONTROL ONLY OF NOTICE: WHEN GOVERNMENT OR OTHER DRAWINGS, SPECIFICATIONS OR OTHER DATA ARE USED FOR ANY PURPOSE OTHER THAN IN CONNECTION WITH A DEFINITELY RELATED GOVERNMENT PROCUREMENT OPERATION, THE U. S. GOVERNMENT THEREBY INCURS NO RESPONSIBILITY, NOR ANY OBLIGATION WHATSOEVER; AND THE FACT THAT THE GOVERNMENT MAY HAVE FORMULATED, FURNISHED, OR IN ANY WAY SUPPLIED THE SAID DRAWINGS, SPECIFICATIONS, OR OTHER DATA IS NOT TO BE REGARDED BY IMPLICATION OR OTHERWISE AS IN ANY MANNER LICENSING THE HOLDER OR ANY OTHER PERSON OR CORPORATION, OR CONVEYING ANY RIGHTS OR PERMISSION TO MANUFACTURE, USE OR SELL ANY PATENTED INVENTION THAT MAY IN ANY WAY BE RELATED THERETO.

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I I I I I I

CONrloKKTIAL

Comporottve Study of Types of

VTOL Transport Aircraft DUCTED FAN DESIGN STUDY

OF THE VERTODYNE REPORT R-80 VStrtol Aircraft Corporation Morton , Pennsylvania

ONR ARMY

Research and Development Program

Contract NONR 1681(00)

Thi» document conlatnt informnilon »Hec ting the nMional defenae of the Unittd Stalat within the meaning of the Capion^gn Law«, Title IB, U.S.C., Sectiona 79) and 794, The tranamlaatun or the revelation of ita contenta in any manner to an unauthoriaed peraun ta prohibited by law.

tieproduction in whole or in part ia permitted for any purpoae of the United Statea Government,

MA WAHL AND 0 T JULIAN

I

1

Supor*n«d by W. * • ^SfH»**^ Approved by

W.l. ITErNlfWSKr Clibl 1*0 LIOOUGIAS Vic« IW- Engin^einQ

Cof^f No COWrtDtNTlAL July 13, 1956

■ ■ .■

■■■.■ .•■

GOIfFIDBHTIAL Pag« 1 Report R-ao

TABLE OF CONTENTS

Figures

I • Siunmary

II. Symbols

III. Introduction

IV. Ducted Fan Concept

V. Duct Design and Limitations

VI. Fan Design A. Design Basis B. Fluid Flow Requirements G. Fan Configuration and Inlet Geometry D. Fan Blading E. Inlet Guide Vane Control

VII. Results and Conclusions -

VIII. Recommendations

IX. References

Table I

Figures

ii

1

2

If

7

9

12 12 12 Ik lh

15

17

18

19

20-37

COHFIDENTIAL

-

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1 1 (

[

I

CCKFimMflU, IM U

1. Static Thrust Characteristics of Ducted Fans Ideal Thrust

I per Horsepower vs Disk Loading Sea Level - Standard Day

2. Flow Pressure Traces

3. Variation in Thrust per Horsepower with Diffusion Ratio for

Several Inlet Loss Configurations

5. Variation in Thrust per Horsepower with Diffusion R&tlo for

Several Inlet Loss Configurations

h. Variation in Thrust per Horsepower with Diffusion Ratio for

Several Inlet Loss Configurations

I I 6. Thrust per Horsepower vs Inlet Pressure Loss Coefficient

7. Exit Velocity <S: Mass Flow vs Exit Area

8. Exit Velocity Pressure & Volume Flow vs Exit Area

9. Variation of Fan Design Parameters with Annulus Ratio

10. Variation of Fan Design Parameters with Annulus Ratio

11. Variation of Fan Design Parameters with Annulus Ratio

12. Variation of Fan Design Parameters with Annulus Ratio

■ 13. Variation of Fan Design Parameters with Annulus Ratio

I 1*+. Variation in Fan Design Parameters with Annulus Ratio

CONFIDENTIAL

- —....

cfmimmiu Hf lit »«»port fl-ao

15' Variation In Fan Design Parameters with Area Ratio at Minimum

Root Radius

16. Variation in Fan Design Parameters with Diffusion Ratio at

Minimum Hoot Radius

17. Horsepower vs Amiulus Ratio for Indicated Diffusion Ratios

18. Inlet Guide Vane Turning Angle vs Thrust for Non-Diffused

Duct at Minimum Root Radius

CONFIDENTIAL

;-*--S ■■■■■.

£,^.~ZZ

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cowrmcNTUtL

I. SUMMARY

The fluid flow principles of ducted fan propulsion are reviewed and developed for several duct configurations. Momentum theory has been modified by duct pressure loss concepts to provide an understanding between duct and fan requirements. The thrust per horsepower capabili- ties are shown to be a function of duct shape and the fan design is inci- dental to such propulsion efficiency; however, for a giver duct a specific fan is defined and required.

For the vertodyne transport configuration of Ref. (1) the thrust per horsepower requirements, fan sizes and required blade design parameters were determined. A perfect bellmouth entry with no downstream diffusion has been assumed as the basis of the fan design.

Thrust control by variable guide vanes has been evaluated and satis- factory thrust reductions have been obtained at inlet vane turning angles between 0 and 20°. Further basic cascade test data is required to evalu- ate the ability to obtain such inlet vane turning angles.

CONFIDENTIAL

—«.

■>. - -

; m ■■ . i *: i ^'■■'--i(^.-:':W ri-. ' ;■■-?■?!■■■ LSJ.A-

i 1 II. SYMBOLS

I

I

Wm%w «

ftp pert i-^O

A Area, ft2

D Diameter, ft

M Mass, slugs

m Annulus ratio, RR/RT

N Number of blades

In Rotational speed, RPM

P Pressure, lb/ft^

Q Volume flow, ft3/sec

R Radius, ft

T Thrust, lbs

- V Velocity, fps

W Resultant velocity, cascade inlet, fps

w Disc Loading, lb/ft2

I CO Rotational velocity, radians/sec

(O Mass density, slugs/ft3

I ^j- Density ratio, P/fo', or cascade solidity

I (3 Inlet angle, cascade

ß. Exit angle, cascade

I Q Turning angle, cascade.

a Cascade angle of attack

0 Cascade angle of incidence

Z Inlet vane turning angle

I I I CONFIDENTIAL

,

0

Subscripts;

A Axial

B Exit

F Fan (or propeller)

I Inlet

R Root

T Tip

U Tangential component, cascade flow

«o Infinity

.»

.

CONFIDENTIAL

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mnmmtii

a*port R"

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1

III. üfTHODUCTIOIt

The objective of this report was to present the operating principles

of free and ducted propellers and then to specifically evaluate the ducted

propeller requirements for the Vertodyne. The words "fan" and "propeller"

are considered synonymous in this report. This entire study has been

limited to static thrust conditions, but could, of course, be extended to

encompass various inflow ratios.

This design study was preceded by a review of all the available liter-

ature on the subject of ducted fans and propellers. Various agencies and

personnel were contacted including the Langley Aeronautical Lab, the Univer-

sity of Wichita and Professor H. B. Helmbold, now of Fairchild Aircraft

Corporation, Hagerstown, Maryland. In addition, the principles developed

and used by VERTOL in the design of aircraft cooling fans were employed

where suitable.

Momentum principles have been used to analyze the flow through ducted

propellers and it has been shown that for a given diameter the thrust per

horsepower of a propulsion unit consisting of a duct through which a fluid

is pumped can be greater than a free propeller.

It has also been shown that the duct defines the thrust per horsepower

capabilities and the fan or propeller is an accessory to the propulsion

unit; the propeller is a necessary evil but need not be considered when

comparing thrust per horsepower capabilities of various duct configurations

(or "free" propellers).

CONFIDENTIAL

■1 .,,:■: v

. ..: :, .

iniiPilliffil

Btport S-80

fher* is a Halt, howpvi»r, to "JM* a*»ßl«»ct or the : rop«»lI#r—that is

thp efficiency of the propeller. In general, a ducted propeller will be

more efficient than a frpp prop^llpr due to the rpduction in tip losses.

This m^ans that flow comparisons made on the basis of pqually efficient

propeller discs either in a ducted or free system will be conservative for

the ducted propeller.

Various duct designs are possible ranging from one which would en-

close the stream tube of a free propeller to an expanding nozzle type.

The difference in such duct designs is the ratio of the ar^a at exit com-

pared with that at the propeller. Momentum principles reveal that the

greater the ratio of AE/AF, the greater the value of T/HP can be.

Considerable emphasis has been placed on the design requirements of

the duct. The duct has been considered as a flow pressure loss (or increase

at the fan disc) system. Inlet losses, for instance, severely detract

from the T/HP capabilities of a ducted propulsion system. In addition,

neglecting the propeller in this case can be quite optimistic since flow

disturbed by the entry can reduce the propeller efficiency.

Diffusion ratio, Ag/Ap, also has limitations imposed by separation

in the diffuser. If a gradual expansion of 7° cannot be maintained, some

form of induced or forced control of separation is indicated. . -«« • •

The duct design chosen for specific analysis for the Vertodyne has

been selected as a non-diffusion duct with a perfect bellmouth entry.

Mass flow requirements were determined and the fan pressure rise and

vector diagrams were thus defined. The required fan was then designed on

the basis of NAGA cascade data, reference L(-.

CONFIDENTIAL

!

1 t

I

I I I I I I I I I •

GCNFimMTlkl

Report H-dO

Thrust control was proposed by inlet guide vanes. Th^ analysis shows

that the thrust can be effectively reduced at inlet vane turning angles

between 0 and 20 degrees. However, no cascade test data is available for

the existing inlet vane cascade situation of & = 0°. Such basic test

data is one of the recommended programs necessary for ducted fan propul-

sion units.

CONFIDENTIAL

^Ä "'

zcmimmfiAh ?m* 7 mport B-BO

if. pypTgD nn coN?ppr

A discussion of ducted fan application to propulsion or vertical lift

may best be begun by reviewing the momentum principles of a non-ducted or

"free" propeller. The discussion will be limited to static thrust

conditions.

The thrust of an. Ideal free propeller may be expressed as

T = M^V (1)

However, since there is no other body for the thrust to act upon except

the propeller, thrust may also be written as

T = AP A PP (2)

Ap ' v ro0 (5)

The ideal fan power is

P = QAP ~ A^&evJ =^PAo0V0.3

i

and the thrust is

T = MAV = fA^v^ C6)

CONFIDENTIAL

Equating 1 and 2

Pr - M^\/ - fCA. V^rV-.-Vo) (3)

The fan pressure rise may also be expressed simply as the required velocity

head developed, or

Equations 3 and h may now be solved for the well known relationship between

Vfan and V^

I I I

mimmiAt

Bmpsrt R«^0

The principle that Thrust Is A function of \ß and Power of %ß is

apparent} by increasing aiass flow and decreasing V^ the basic "improvement"

in T/HP referred to in ducted fan propulsion is obtained.

The following specific equations may be developed:

For constant disc loading yHPD DUCTED

yup PRE£- \ (7)

!

I I I

For constant power and disc area

1/ HPDUCTED

VHP FREE \

2 JZl. (8)

Thrust per horsepower capabilities of propellers based on the above

momentum considerations are presented on Figure 1. The area of helicopter

and aircraft propeller operation are noted and one set of available ducted

propeller (reference 6) test data* is shown. To incorporate such data

conveniently, Figure 1 is at standard sea level conditions.

I I I

♦The included ducted propeller tests are based on reference 6 by Robert J. Platt, Jr. Discussions with Mr. Platt have indicated that the propeller-duct combination was not necessarily operated on design.

I CONFIDENTIAL

- »MNB - ■-»

smrimmiAL

/. 'jvcr PFSIG*? WD ivn^xru:'*

That an L-nprov^ment in T/HP can bo obtained by shrouding a propeller

of a giv^n diameter and thus controlling the downstream flow contraction

Is well known, but it can be shown that an improvement can be obtained

only by use of the correct duct shape; improper ducting can decrease T/HP

compared with an equal diameter "free" propeller.

It therefore becomes apparent that the duct design is the basic issue

and for a specific duct a fan is then defined. It should be mentioned

here that it is too much to expect that a given fan can be evaluated as

being "better" or "worse" in or out of a shroud; the fan must be designed one

forAinstallation and could be completely off design for the other.

Such thinking leads to the obvious requirement of an understanding

of the inter-relationship between duct and fan. This may be most easily

visualized by considering the problem as a duct-flow pressure loss prob-

lem. Figure 2a, b, c and d pictorially present the traces of total,

static, and velocity pressure which would occur through several duct

configurations (including a classical "free propeller"). It can be seen

that the pressure rise required through the fan is equal to the down-

stream velocity pressure plus, as in Figure 2d, any other penalties such

as friction or entry losses.

To show the seriousness of such additional duct losses. Figure 3

presents thrust/horsepower for a fan of the Vertodyne configuration size.

With a perfect bellmouth entry the expected gain in T/HP with increasing

ffusion ratios is apparent and at a diffusion ratio of 2:1 can double di

- -

CONFIDENTIAL

- * w ■

i <

:

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izmtKL

the T/HP of a "free propeller" of equal diameter and efficiency.

Actually, Figure 3 has been based on fan efficiencies of nominally 100%,

Since a ducted fan of such an RR/RT can be expected to be 90% efficient

while a free propeller may be more nearly 80% efficient, an increase of

more than twice the T/HP of an equal diameter free propeller may be deter-

mined In testing. It must be remembered that to provide a diffusion ratio

of 2:1 either (1) a long diffuser of about 7° included angle must be pro-

vided, or (2) separation must be prevented by induced or forced circulation

(boundary layer control). The power requirements to the aircraft (such as

turbine bleed) of any boundary layer control system would need to be

evaluated against expected diffusion gains.

However, Figure 3 also presents the variation of T/HP for ducts having

varying degrees of entry losses. With a loss of only .25q the duct is

I hardly better as a lifting or propelling device than a free propeller of

equal diameter. With an entry loss of .5q (which is representative of a

i sharp edged hole in a flush surface such as a wing) the T/HP is less than

a free propeller and actually gets worse as mass flows are increased by

providing greater diffusion ratios. The use of a simple tube entry where

f AP/q approaches 1.0 can provide only 1/3 the thrust for a given horse-

power than a free propeller of equal diameter 1 Even worse, such entry

losses can provide disturbed flow to the fan and further decrease T/HP

due to loss in fan efficiency.

Figures *+ and 5 present the thrust per horsepower requirements of the

Vertodyne if the fan area can be increased. The obvious advantage of

increased fan area is readily apparent and simply reiterates the basic

CONFIDENTIAL

#*

9% »Ist

SP U {11 .-

principle of the aivanta^s of lauer disc loading. Figur« 6 nas teen

cross plotted froci the abovp iata specifically for a 1:1 diffusion ratio

duct. It zero ontry loss conditions thrust per horsepower can bp Increased

U-0% if the fan annular area can be doubled.

■

CONFIDENTIAL

:- ■. ;.-■■■..■..,

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on !.-

VI. FAN 3^10::

A. Design Basis

In order to present the fan design requirements for the Vertodyne

transport (reference 1), the following assumptions were made:

1. Duct entry will be an ideal bellmouth. No flow energy

losses.

2. Diffusion will be accomplished with no separation.

3. Available cascade data (references 3 and k-) may be extrapo-

lated where necessary, although design will be held within the

range of available cascade data where possible.

The design conditions are:

Altitude 6000'

Ambient Temp. 950F

Gross Weight 112,000 Lbs. (approximately)

1 B• Fluid Flow Requirements

• Mass flow requirements were determined for various exit areas and

the fan pressure rise was determined from

The fan flow parameters are plotted on Figures 7 and 8.

G. Fan Configuration and Inlet Geometry

Two fan speeds were arbitrarily selected:

W, = 800 fps

W| = 900 fps

CONFIDENTIAL

mmmmm report H-80

This was don«» to prßclud" the possibility of sudden drag divergence

at high subsonic Mach nurabprs. The fan was considered to consist of

an inlet stator (or guide vanes), rotor, and exit stator. The inlet

guide vanes were set at zero for the design condition, but were con-

sidered in Section TT-E of this report as the thrust controlling mech-

anism. The fan inlet angles, required turning angles and required

powers wer^3 then determined for various ratios of m(m = Rroot/Rtip^*

These data are plotted on Figures 9 to 1^ for three different

divergence ratios, Ag/Ap = 1.0, 1.5 and 2.0. The limiting value

where the root inlet angle ßIR equals the required turning angle

has been determined from Figures 9 to 1^ and as such has defined the

minimum RR/RT; this provides the greatest fan annulus over which con-

stant pressure blade design can be provided.*

The resultant values of ^ root} ßt tip» 0 root» ©tip» Vaxlal,

RPM, Power, and m have all been plotted for the minimum value of m vs

diffusion ratio on Figures 15 and 16.

No fan efficiency has been Included in the required power, "air"

horsepower only is shown, but the effect of decreasing annulus and

diffusion ratio is apparent in Figure 17. Substantial gains in T/HP

are apparent with increaslnp diffusion ratio, but the effect of

annulus area rapidly diminishes below RR/R^ of about 0,3,

♦Constant pressure blading was recommended in discussion with NACA personnel at Langley Aeronautical Laboratory in view of downstream mixing losses. Testing may Indicate a larger gain due to increased annulus than losses due to downstream mixing but at the current state of the art constant pressure blading appears to be a logical first estimate.

CONFIDENTIAL

■^ iiiiMmLiiiiiwiwwMMi) ■■-- in mm^^mmmmmmmmmmm^mmmmmmmt^mmmmmmmmKmm^m

.r ort S-

D. Fan BladmK

The first practical application of ducted fans for static, verti-

cal lift might well hp based on a diffusion ratio of 1.0 (inlet area

= fan area = exit area). This may be done to preclude the variables

of diffusion separation control and has been considered for the

continuance of this study.

For ^ß/Ap = 1*0 the required fan blading has been determined

from references k and 5- These data are presented in Table I.

E. Inlet Guide Vane Control

Two possibilities of fan thrust control are (1) collective pitch

control of the rotor blades and (2) inlet guide vane control. Inlet

guide vanes have been considered in this study due to the inherent

mechanical simplicity of such control compared with collective pitch.

The inlet vanes have been assumed capable of turning the flow by

various amounts and the resulting pressure rise through the vanes,

rotor and stator have been calculated. A balance of fan AP and exit

velocity pressure define the thrust output. Decreased thrust only

has been considered, the fan having been designed for a maximum static

thrust of 112,000 pounds.

It should be noted that the inlet vane incidence angles required

to produce the required inlet flow turning angles was not determined.

Test data for cascades at inlet angles approaching 0° will be re-

quired to estimate the inlet vane incidence angles. The maximum

turning angle (Z ) required to reduce total thrust from 112,000 lbs.

to 8^,000 lbs. is 16°. This would seem to be a reasonable value.

L Inlet vane turning angle is presented vs thrust on Figure 18.

CONFIDENTIAL

:

. mm .- - — - . , _ , .

... I ■ . ,.■..

^OMFI^fTlÄf*

%port 'l-SO

VII. RESULTS AiVD C0N'JLU"ICr:3

An aircraft with two ducted fans located in the wings has been

studied to evaluate the type of fan and duct required to provide a hover-

ing ability at 6000' pressure altitude, 950F ambient temperature. The

following specific conclusions may be listed:

1. For the disc loading of the 112,000 pound Vertodyne transport

with 16.7' fans a properly ducted fan can provide a Thrust to Horse-

power ratio as great as 3*8.

2. Details of a ducted fan installation intended to provide

vertical lift are as follows:

a. Momentum theory appears applicable when modified by the flow

pressure loss considerations of the duct.

b. Inlet design requires a "perfect bellmouth". Severe decrease

in T/KP results when inlet pressure losses are encountered. For

the subject aircraft, an inlet loss of ^ P/q = ,25 results in a

ducted fan of essentially no greater T/HP than a free propeller

of the same diameter.

c. If fan disc loading can be decreased, a substantial increase

in T/HP can be obtained; increasing from a maximum value of

3.8 lb/HP at a disc loading of 292 lb/ft2* to 5.5 lb/HP at a

disc loading of 1^0 lb/ft2**.

The above figures are based on a downstream diffusion ratio

of 2:1.

♦Subject configuration; G.W. = 112,000 lbs., Ap = 2(190) = 380 ft2

**G.W. = 112,000 lbs., AF = 2(^00) = 800 ft2

CONFIDENTIAL

I I II III-

I I 1

-cmniFffiAi»

Upport i

d. If downstr^ae dlffufion is llslt^ci to 1:1 (kfg^ ■ ^exit^f

which may b* a practical installation, the maximum thrust per

horsepower for the subject configuration is 2.7 lb/HP. A

decrease in disc loading to ikO lb/ft2 can provide an increase

in T/HP to a maximum value of 3-9 lb/HP«

e. For a practical 1:1 area ratio duct, the following detail

data have been determined for the Vertodyne:

(1) Thrust per Fan = 56,000# @ 6000» @ 950F

(2) Fan Outside Diameter = 16.7 ft

(3) Fan Inside Diameter =

C^) Fan RPM

(?) Horsepower per Fan =

f. The thrust per horsepower of this practical 1:1 fan is

estimated to be at least 50% greater than a free propeller of

equal diameter.

5-9 ft

919

20,200

I GONFIDF.NTIAL

■ .

mmmmmmmm wmmm

MPW« •

I 1

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I

:«m^!tTi4L 17

vui. mcoM^npnTicns

l, Ti»st programs to evaluate ducted fans should be initiated. A

recomnpndpd procedure might be:

a. Determine flow characteristics and pressure losses of the

duct without a fan with duct modifications as required.

b. Determine fan efficiencies by testing the fan alone per

ASME Standards with fan modlflcatinns as required.

c. Evaluate the fan In the duct.

2. Extend the range of cascade test data now available. Inlet

angles approaching 0° should be evaluated for thin symmetrical air-

foils for use In Inlet guide vane design.

3» Extend the range of cascade tests to provide Inlet angle data

lower than 30° for 65 series compressor sections.

CONFIDENTIAL

I I.

ix. BB3MBM

I

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zcmFimntiki Pag«» 18 Report R-SO

1. VERTOL Report R-76; "Comparativp Study of Various Types of

VTOL Transport Aircraft - Configurations Studies" -

May 1, 1956

2. Helmbold, H. B.; "Range of Application of Shrouded Propellers"

Fairchild Aircraft Division, R221-011 - August 1955

3. Stone, Arthur; "A Study of Shrouded vs Unshrouded Propellers"

BuAer Report No. DR-1750 - July 1955

h. Herrig, Joseph L., Emery, James C. and Erwin, John R.;

"Systematic Two-Dimensional Cascade Tests of NACA 65- Series

Compressor Blades at Low Speeds" - NACA HM L51G31 - September

1951

5. Felix, Richard A.; "Summary of 65- Series Compressor-Blade

Low-Speed Cascade Data by Use of the Carpet-Plotting

Technique" - NACA RM L5l+Hl8a - November 195^

6. Platt, Robert J. Jr.; "Static Tests of a Shrouded and an

Unshrouded Propeller" - NACA RM L7H25 - February 19hS

CONFIDENTIAL

TABU? I Hgm 1$ R#port H-

FAII DATA TAPULATIi CAE/AF = 1'0^ ^ = O.ÖÖ178 31ugs/Ft3

For Miniaium Root Radius

wlt = 900 fps wlt 800 fps

FAN STATOR FAN STATOR

Dtlp» ft 16.7 16.7 16.7 16.7

m 0.355 0.355 0.M+ O.Mf

Droot, " 5.92 5.92 7.35 7.35

No. Blades 9. 7. 9. 7*

U) 96.1 81.5

n - rpm 919. 778.

TIP:

Airfoil 65-^10 65-(15)10 65-710 65-(17)l0

<r 0.5 0.5 0.5 0.5

B 3.2° 13.95° 5.60 17.0° oc ifA0 7.7° 6.5° 10.3°

/3. 63.3° 13.95° 58.2° 17.0°

0 31.1° 83.7° 38.3° 83.3°

Chord, ft 2.92 3.75 2.92 3.75

ROOT:

Airfoil 65-(17)10 65-(17)10 65-(17)10 65-(17)10

cr 1.5 1.5 1.5 1.5

e 35.05° 35.05° 3^.9° 35.0°

ö< 20.10 19.9° 19.0° 19.9°

/$. 35.05° 35.05° 35.^° 35.00

<t> 75.0° 7^.8° 73.6° 7^.80

Chord, ft 3.09 3.98 3.85 ^.9^

,*, — . —-a— ■—

CONFIDENTIAL

■

•V "I^W.^P #"«^:miK9 * A^* ft*

JUport H-SO

M

CO

5

•H

'S

m

o tX) vO CO vO CM

JH/scn - aartodasaoH aad ^.sruqx

GO^IDENTIAL

CONFIDENTIAL

( iMim

Wm# mm Bmport R-HO

FIGURE 3

VARIATICN IN THRUST PER HORSEFCWER VITH DlFFUSICff

RATIO FOR SEVSRAI, INLET LOSS CONFIGURATIONS

"liimpi

56,O0(#

192 ft2

w = 291.7#/ft2

/^ = 0.00178 alugs/ft^

§

5.0 I—1—I— 1 1 .1 1 1 !• 1 1 1 1 1 1 1 1 1 1 1 1 1

1 1 1

. i 1 i ii:

4.0 — [■—-

[—.,. .~.. U—. — ,<

h^ ^^

■: —. i ^r —

r

^ ^ -' r ■|""f M

■ _^i*i zz —"■ II ..1 3.0

iwT j~Lir ̂ a*]

= T* .P/q)Es 0-l0l

i' 1

—^ „ .... .«— /A T, / V

! 1 ' ■ ::

.-,^,J ... ^r/QJ* m D-?«rn

' »— j Wt 2.0 Äfl ■»»«

; i {

J -J -»«

1 ill im *l

1 -H u P/q si' j

~n il n ̂

«1 -. ^

rjfl UH ■ < ̂ P/n\^t'^i ji 1.0 l 1 T*Tr| "1

' T a - x,u Ti

' ! ' : :: ! ' ' | , 1

i i

: ; ' ! 1 ' ' i' • ' 1 j i]

0 :; ' ni ! j ■ ill ■ 1! ' j j ■ yj

; ! ' j ■ j ! jj |

1.0 1.2 1.4- 1.6

AE/J

1.8 2.0

'AF

CONFIDENTIAL

, • -

ut

»•pert %-SO

FIGURE 4

VARIATIOW IN TWJST i'j£R HORSSI'CVSH V'lTH DIFFUSION um rm menm nnjsr LOSS ccKFiouR/iTioNs

T

AF

561000/

300 ft2

v = 186.6y/ft2

/^^ s 0.00173 slugs/ft3

2.0

CONFIDENTIAL

i

r.1 : i

_. I

1 I I I

SQPlMHIlt f*g* Ü «•pert 1-iB

■* 'V-'

FIGURE 5

VARIATION IN THRUST FER HORSEPOWER WITH DIFFUSION RATIO FOR SEVHUL INLET LOSS CONFIGURATIONS

T = 56,OOC^

AF = ^00 ft2

w = UOlf/f t2

/O = 0,00178 slugs/ft3

I [ I 1

£

I CONFIDENTIAL

c«rfs«frut

■•port ft-#0

riGÖRE 6

THRUST PER HORSEPCWER VS

INLET PRESSURE LOSS COEFFICIENT

T = 56,OOQj<

/O a 0.00178 slugs/ft3 lE/AF = 1.0

1.0

(A P/q)E

CONFIDBNTIAL

^ ---:-"r: -'m .-; :■:■«>■■..■.:.[;■:■■ ■^rm^:r,^^v. .,-.„-..-■■ -V„n-W : ■

I

I

(

i I

[

l l

a I

•r)

8

AOO

330

360

320

280

260 200

COiriOUfTlAL

FIGWI 7

KIT VELOCITY 4 MASS FL» VS EXIT AREA

HB port I-ÄO

250 300 350

Exit Area - Ft2

CONFIDENTIAL

400

■\ L

T-

1 1 illfnl 1 1 1! ■ 1

! , i 111! 1 ■ 1 ■ * ] T

1 1 • 1 y K

Alt = 6000« QAT = 95*^

1 y / 1 £xSJ

1 \J K \\ i I; i —

i \ \ i: v K * 200

V:: '; j; y

V y \

L_ ■ /

1 ;; \ Velocity / /

190 \ i

—■

A / Mass |

\

■

/

.-...■ 1

? \ v. / ;;;!

CO 01

\

......

J / isoi

\ ' IJ / •

N A ^

%

f \ CO

i A V 170 If •

/ \i"\ ; ,

J f N i N ;,[

1 N 160 l

A /

\ A N /

f!|T

....- ..,..,_ —J \ h, i ll \ Ik 150 7 *

4444- \

S. ' / f 1 i'

^ v / ill

• HT _.... i; 11 ;;' ; 1! i I.' ill m« N.

_ ■

" ■■■'■"

"UO A50

■....■.„:■■..■■

niwiMmn »•port Ä-«0

riOÜRÄ 8

EXIT VELOCITY PRESSURE & VOLUME FLCW VS EXIT AREA

UO

120

I 100

i

a <3

80

60

1 i'' :: ■■—

1 Y 1 ..>_.

IT =56,000 lbs * /

CAT = 95^ s iffi . — u

x '

V I 1 '; i

y >r ili

! , ' ■ /

^_ h 1 1

■"-

WP i ■ I > vo:

' | ■ ; ■ i.

1 ' ! . y /^ .umf » . 1 i 11

1 \ / - ■ 1 \ v V

/ \\\\ . !

\

V y S

: i 1 i

>

'■''■'<

/

^"* T'TH \

l:lj

/ s ̂

/ V X i 11 i ::::

■ 111 {

/ X .. :

■':'.',. f. Sw

iil! ii jl ^> 4L liii 'ill

^ isl *^

lijl \\\\ ""•s; ItH

120

100

90

80'

70

o H

O VJJ

200 250 300 350 A00 A50

Exit Area

CONFIDENTIAL

_ t

zimiömn*i

ricü« 9

VARIATION <P FAN DBSION

RUHuanna nni A>INUI;JS HATIO

I m

l

1. i

OS

i l

80

AVAI

T Rtlp

s 1.0 Wltip = 800 fP3

56,000#/fan f> = 0.00178 slugs/ft3

8.35'

60

AO

20

1 ■- i i i.. 1 1 1 r i J ! 1

1 1 1 i 1 k« • 1—" — L,_ —

r ! D 1 L 1

i r~~«.

_...., — ---• i i . ri

0, root

^ >^- — )~\ i~~i —< ^

— yfi

— _ ■ ■ ^

1 ^ ) ' . * t . i

i i ■ i !

■i ■' ' ~l 'H" i • "4

i , ©tip ^ -A H"

0.3 0.4, 0.5 0.6 0.7 m

!

1 cn

I

0

540. """l *T^1 ̂ ^ ^w —^ M»M

VA

>

r82( J «^ i

- N /1 as"

1 _

-H --- —- M, /

^80 •r-fi

TS- >v ^/ ̂ s

■W )__

...... ^ ^<

JP

^ ^ ^ »

^ ^ s

-•■ rrH » - i-4

1 ^

>. ; ■ \

/90 ^

v> -

l66i D -

0.3 O.A 0.5 0.6 m

GOIIFIDENTIAL

0.7

29

25

21

o

. • ■■■ - ..- ■ .«« ■■■ • •

———

eomtommi

nomE io

VARIATIff JF Km DSSIOH JAHAMSraiX Um Ä»'MULUS KAT3 ;

(0 «) 0) U b0

I

<u H

80

äVAF

■ 1.5

T - 56,0)0//fan Rtip ■ 3.35'

wltlr . 800 tm

p = 0.00178 sl'Wft?

60

^0

20

—- T~" I

L... ..„ j

_ ■ 1 'i ■•

-., ! [ ! ^ «P

' ""- ■K — -— —

i

— I 1 1

1 ' 1 - 1

1 1

) i .i,

-•5

— i

1

\

•

\ ^ e? ^oot

' ■' 1 .

' I ' .

■ 1 1 1

. e TIP :

—: wWill '

! r i . in -,.1

0.2 0.3 0.4 m

0.5 0.6

I

m

CONFIDENTIAL

i ^

o

■HM

I : miu*r:Ai

FIÜURS 11 Report Ä-HU

I VAJUATIUN ÜF FAN USSIOH

FAHAMhrrivRLi WITH ANNULUS RATIO

AE/AF a 2.0 T = 56,000///fan Rtlp --- 8.3f'

Hip ■ BOO fps

s 0.00178 slugs/ft^

(0 0) 0)

M

0)

c

(X

l

ÖU

~ 1 S&, 71*'.

7 ' 1

■ ■ i i f 1

60 1 i 1

.... L i . t f-R 'S Koo^

„„. -^ r \

1 : ■

1 i '' ^0 1 >>

\

/ x'

,

1 i i

■ "i

^ M

N-J -„- —i

20

TS

7 ̂ 1 o -_-

^^0 t ! - M -J

^ ? Tip u ■~l —1 —J , 1 ,,,,.. J

0 [ rrr i i ' i i ,::!., ! —i -j 0.2 0.3 0.A 0.5 0.6

0,2

m

.>//J]

H . H

■88 P""

M V K x

-*— *tfr ^

s r-

i 300

*-* ̂ i > <d ■ 8^ •ou

^

-^ ""■^

y !6.^ i)!l

|.u.j4 : •" • v f ->• vs '

26t) i 8C )0~ 0.3 0.4 0.5 0.6

32

28

o

m

S.- CONFIDENTIAL

. :•• - • _

cmitmrruL

riGim 12

VARUTION (F FAN DESIGN M/UÄTms WITH ANHÜLUS IttnO

AB/AF

Thruat Rtlp

1.0

56,0000/tun 8.35'

Wltip . 900 tm

/* m 0.00178 al^ga/tt^

.«?***» .*»«wt ■

. ;^.. :,, , .

I fwm i?

Thruat = 56,(>JO//fan Z^7 « 0.0Ü178 slugs/ft^

Htlr » 8.35'

10 0)

I

0) H

-4

in

i

m

%

o

CONFIDENTUL

■ . — — . - -

*

V)

8 u to

I

0)

<

iOWSMMSit

riGtii« i4 ■ipirt M9

VAIU*TIC¥ I» FÄ» DBSICÜ rARÄ^!E?»»S Ulli imnui RATIO

ÄE/Ar =2.0 «Itip'Wfps Thrust ■ 56,0CN>//f8n /O = 0.00178 olugs/ft3

Rtlp = 8.35'

CO a. u i

3^0

300

260 0.2

■ ■"*'" -—

/

•10( D0- —«i

^ s

rrrfis -. . . VT VA ^ X ^"

, § ■ ^ ̂ ^ srfv»1

■98( 3r-

•-:- —- ^ >^

>- > <

^^ ^

V5 > * ^ S " .

i|

■fH*

rfT" ̂ ^ ■ ■ 1

I ' * -■ ■-;-_ ■***■

4rt ifff ; ■'

■^^

!.„„ r^ K i&i. '■1

LL._ _ ^96 0— [1 , Ll,

0.3

36

0,4 0.5 0.6

32

E9 H

28

CONFIDENTIAL

— »- ■

i . - ■—■ _ • ■■■--

- .

■

:

öaifiiÄriÄi

n^m is VARUTICH IN FAH DESIGN PAHÄMSTERS WITH

AR£A RATIO AT MINIMUM ROOT RADIUS

I

in

i to I i

0) H

T ■ 56,000^^11

Rtlp = 8.35«

80

60

^0

20

Wltlp " 800 fP8

•** = 0.OO17B slugs^t3

r _. _., i ! 1 ! i i

L 1 |

...

t '

^ UP :"l-: L rr-

■--

.— | 1

-r.. j, ,..

....

! 1

—.-, _.- —

1

! i

... ! —1 ^ Root I

; i „UJ -—

....

! 1

i "''' ——

8 Root p ^^ —. ■MM. ■""^

i

i

r

1

-jU. ■ —

^t*

1 1 Q rip

St —< T ^.

rt =3 -] —. =

1.0 1.2 1.4 1.6 1.8 2.0

i

1

10

I

450 —- — — "P —

1 '■ "'

.,..-

0.« | ^^PW

S^ 4= % ^

^

in

k VA

^v.

_.,. .-.

350 Htfi, "^ 0..

_ I^t **-*,

% T-Li —pf

'HP ^b

^ (2: ^an ,)

.... .... ••- ,.., .... 3E t=

250 _ o.: 2_ 1.0 1.2 1.4

45

3

35 VjJ

1.6

AE/Ax

■ .■

C0NFIDKNTIAL

g

1.8 2.0 —J25

mm

cariösm*!

riGum 16

VAWATIOM I» FAN DESICIt «RAKSTERS WITH DIFFISION fttTIO AT MIMIWJM ROCT RADIOS

Thruat ■ 56,000#/fan

Rtlp ■ 8.35»

wltlp " 900 fpa /O = 0.00178 sluga/ft3

2.0

o«4rni u

Afi /Ay

CONFIDBWTIAL

-■

— —. ... - -I-**" M

I I

larai

FIOOTB 17

HCR5 «OWBR VS AfWULuo RATIO FOR INi/iCATED DIFFUSION RATIOS

T s 56,OOCtf/fan

Rtlp a 8.35'

^ = 0.00178 aluga/ft3

I j

I I !

!

I. L I

CO c

I

? o

?w fljT I [ 1 f 1 ' ' ' i n i 1*1' j r "ypiw

1 *■ 1: 'ii !::

I''' N 1'; 1 1 I 1 1 I ' 1 ' ' ■ j 1 111 y 4 lii 1 < 11 {

hin 1 • ' 1

-rrr ill 11(1

! ii | 4 1 | {

"Trh 1 i:|l

11 ' j i ■ 1 ' ' ' i ItH

> 1 46 UJJi Mi In.

1 t M ' iiiii 1 Ittft | J j! j

!ill 1

11 f 1 i |!| Hill

1 | i | i

Ii P ! j j! 11 *' IJJjj IIII d 1 jiiii flfn ijttf i ■ • • i

1 :i nil .J UJ

111 i !!i! 1

1 ■ i 11! il ! ' 1 j j ] ] 11

1 1 1 1 111 I ! <; 1 1 M | i . . i

ttflt III if m

i l

: ' i i II 1 ) • 1

KM lii! 1 1 M

rHfi I'M

II 1 II

Hrr* i j 1 i j ! j 111 1 m Mil

| ■ i . ■ II iii' i

1 1111 11 II iii I i j [nmi.iiiimnnM

) :ii hi iiif %

frTT!

iiii iiii

42 t

i Ü ' 1 ' i i ii t i 1 * VAj r ij] jr. iii 1111

|| i il r-rr T

i . i

■ ;; < ! i ! . i i

. i

iff k> \ ', ! 1 ■ '

i i'i • i t '

■i j l

| [ \ I i t 1 t i

' ' 1 ■ ! 1 I < i ii >r ̂ i\ ■r^

1' i - i

; i: | |; 1 1 1 ! 1 ' ■

i ' i » f-f-h r fr

' 'i

- 1 i • • r • i <

' i1

iii 1 1

iff

«• i

i*jfl IHT • i'

1 !' i i

> ■ . 1 i ;| | I ! ii Ls\ >««**i ! ii

■

i II ■ 1 il ' \ \\

in i ii 1 1 • ' j iii

||

JT \

'■ ' 1 "^8 t 1 Tn 1 ! ' 1 ■ '

1 TT] JJO | ttfl

! ii 1 H! ' UJ

Ttt , li!

1 ; ii ■■■jr

ii : i

t M

i 1 ' i i j i i i i it i ttl

1 ii : i 1

Um ffjt • Hi t } i i; ' '' TTn

: ii : n

11 i ■'

iiii J 1 L J

i :i 1 i: : :. 1 i HI \ • { ' 1 \ ]A ii ffT

i ii ■ H

i LU \ ■ j t (

1 i i i i J M

* i : m iiiiHiniimiiijjj

AE/AF '1-5 Ü

1 ni 1 ii i !;

1 1 '

i Ü

! I : ftn i 1 ' 1 34

1 1 1 ;M ■

' 1 !

i ' 1 '11 ! '' 1 ! ' ' ' 1 >^ 1: ■! M

tA

! ■ ' ' ' 1 I!

; 1 ■ 1 Tni

tftll 1 1 ! ! ii ||

fil ' ' • [ I j ' ' ' M 1 l| ttn

i^-pn TTll ■MTI irn

iJil \i > '' i * ''

+T-H "^ f tn **Jm

: ■: 1 in It! 1 !i : n iiW m T^! 1 11 ■

i ii rrrj i 1 M

I | 1 1 : . |i 1

10 ' i i' 1 1 !

* J F 1 \ '1 1

1' i | AE/AF = 2-0 i

1 ' 14j| ̂H t i [

1 ■ i

i i ! il ' pi

1 Ijl 1 n i iii

: ' M ! \ \\ I 1

**H s J W\ i ^i ii 1 ill i y \ i iii i ii ' 11 > 1

i i i I : ! 11 ! ii fill •rrrt. iiftl TTll ' i

: 1 fl 11 i ::

TTii

■ !

ttx i" :i! I "TT

i Ii! TnT i IP r Tn

i i , t M 1 1 i ; i i'i ! i

26 1 1 !l I ii ill i i i

. I 1

T ]fi Tit 1 \ 1! || i !: j Ijl ' '

i [ j i i iij ; i M

0.1 0.2 0.3 0.4 0.5 0.6

1 CONFIDENTIAL

1 ,■■.'■■■.:.:■..-:, -.-,...,.,,:,,,..,-,::.. , .-..-,. _ _ .,,,

.. ■ ..

:*ir.- ^^

CIIFIDr/TJAL Hg9 37 Report R-SO

FIGURE 18

INXST GIIIDi- VANE rüRNING ÄNGLS 7S THRrJST FOR nOR-DIFFUSED D'JCT AT MINIMUM ROOT RADIUS

Rtlp- 8.35' /<=? = 0.00178 slugs/ft3

20°

16C

12' w

M (D a i

eo 8<

1 ■

1 |

|;

I

f-H— i

1 ■■:"■■;

i i : i ,: i i: 1 ' ■•!

i T

1 ■ 1 1 . ; :j ■

i i

i

—,-.^^J-^. ■

i

1 1 ^x

1

1

,„_:.„. i 1 ; \ v

l

hi .i . ■ i ■ .1

... i.

■ ■ '

| ■

1 I

\ i 1

^ '-

— ,' ■ : ' 1 [ ■ 1 ' ' 1

j

i \ ; ■

1 i-™-..

1 ::: ■'ii

i V --. WT = 900-

WlT a 800-

•j

1

i i ■ 1 j \

i L

::: ; : ;; ;i

t

■i \ 1

i. i .. i

i

! ... ■ ■ .1 ': '

1

. 1 !

_ .^

I ■

.,,... ._

\ | i ■ i

1 1 1

i 1 N i' ■ i

i

.1 ■; . 1 ■ I 1

., ,,..„

\ |

... ,

■ i

! , '. i.. 1 : \ i '

1 ' j ■

■ : | li ;:' ■

1 ' [ 1

1

i\ i

i ,, , ' ! ■:;

\ • i;

1 . . i

[ ; - !\ i

■ 1 1 ■ ; I

i

....i.,„.l i ] i

i w ,:

60 70 80 90 100

Thrust - 2 Fans x 10-3 - Lbs.

110 120

■ .

i

CONFIDENTIAL !- ,

firmed Services Technical Information Agency Reproduced by

DOCUMENT SERVICE CENTER KMOTT BUILDING. UUULL OHIO

NOTICE: WHEN GOVERNMENT OR OTHER DRAWINGS, SPECIFICATIONS OR OTHER DATA ARE USED FOR ANY PURPOSE OTHER THAN IN CONNECTION WITH A DEFINITELY RELATED GOVERNMENT PROCUREMENT OPERATION, THE U. S. GOVERNMENT THEREBY INCURS NO RESPONSIBILITY, NOR ANY OBLIGATION WHATSOEVER; AND THE FACT THAT THE GOVERNMENT MAY HAVE FORMULATED, FURNISHED, OR IN ANY WAY SUPPLIED THE SAID DRAWINGS, SPECIFICATIONS, OR OTHER DATA IS NOT TO BE REGARDED BY IMPLICATION OR OTHERWISE AS IN ANY MANNER LICENSING THE HOLDER OR ANY OTHER PERSON OR CORPORATION, OE CONVEYING ANY RIGHTS OR PERMISSION TO MANUFACTURE, USE OR SELL ANY PATENTED INVENTION THAT MAY IN ANY WAY BE RELATED THERETO.

, ■

^

■«•r

UNCLASSIFIED

UNCLASSIFIED