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i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq :E I-- ¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE AT MACH NUMBERS OF 0.8, 1.3, AND 1.75 Donald L. Kassner and Brian Wettlaufer Ames Research Center Moffett Field, California 94035 July 1977 https://ntrs.nasa.gov/search.jsp?R=19770021127 2020-06-13T16:45:22+00:00Z

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Page 1: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

i

NASA TECHNICALMEMORANDUM

NASA TM X-73,218

00

oq

:EI--

¢/3

z

AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED

MISSILE AT MACH NUMBERS OF 0.8, 1.3, AND 1.75

Donald L. Kassner and Brian Wettlaufer

Ames Research Center

Moffett Field, California 94035

July 1977

https://ntrs.nasa.gov/search.jsp?R=19770021127 2020-06-13T16:45:22+00:00Z

Page 2: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE
Page 3: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

I Report No. _ 2. Government Accession No. 3. Rec0pient's Catalog No.

NASA TM X-73,218 l4 T,tie and Subtitle

AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLEDMISSILE AT r_CH NUMBERS OF 0.8, ].3,AND 1.75

7. Author(s)

Donald L. Kassner and Brian Wettlaufer*

g. Performmg _ni_tion Name and Addr_

Ames Research Center, Moffett Field, Calif. 94035andARO, Inc., Moffet_ Field, Calif. 94035

12. S_ns_ing /_cv Nama _d A_r_

National Aeronautics and Space AdministrationWashington, D.C. 20546

5. Report Date

J_ul y, 19776. Performing Organization Code

8, Performing Organization Report No

A-695610 Work Unit No

505-11-4111. Contract or Grant No.

13. Type of Report and Period Covered

Technical Memorandum14. Sponsoring Agency Code

15. Sup_emamtary Notes

* ARO, Inc., Moffett Field, Calif. 94035

16. Abstract

A typical missile model with nose-mounted canards and cruciform tail sur-faces was tested in the Ames 6- by 6-Foot Wind Tunnel to determine the contribu-tions of the component aerodynamic surfaces to the static aerodynamic character-

stics at Mach numbers of 0.8, l._and 1.75 and Reynolds number of 6.25 x 105 ,ased on body diameter. Data were obtained at angles of attack ranging from 0°

!to 24 ° for various stages of model "build-up" (i.e., with and without canard_nd/or tail surfaces). In addition, two different sets of canards and tail sur-faces were investigated.

For the canard and tail arrangements investigated, the model was trimmable_t angles of attack up to about 7° with canard deflections of about I0 °. Also,the tail arrangements studied provided ample pitch stability.

17. Key Words (Suggmted by Author(s))

Canard-controlled missileBody of revolutionBody-canard-tail configuration

19. Security Oa=if. (of this report)

Unclassified

18. Distribution Statement

Unlimited

STAR Category 02

_. Security Clauif. (of this _) [ 21. No. of Pages

Unclassified [ 255

"For sale by the National Technical Information Service, Springfield, Virginia 22161

22, Price"

Page 4: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE
Page 5: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

CONTENTS

Page

SUMMARY ............................................................ 1

INTRODUCTION ....................................................... 1

NOMENCLATURE ....................................................... 2

TEST FACILITY ...................................................... 5

MODEL DESCRIPTION .................................................. 5

TESTING AND PROCEDURE .............................................. 5

DATA REDUCTION ..................................................... 5

RESULTS AND DISCUSSION ............................................. 6

CONCLUDING REMARKS ................................................. 8

REFERENCES ......................................................... 9

TABLES

I.

FIGURES

I.

2.

3.

4.

5.

6.

°

.

Dimensions of Control Panels ............................... I0

Axis System ................................................ II

Control Panels Sign Convention ............................. 12

Basic Model and Components ................................. 13

Model Photographs .......................................... 17

Body-alone characteristics .................. Data Figure Page 1

Body-tail characteristics, main balance and panel loadsummations .................................. Data Figure Page 7

Body-canard characteristics, main balance and panelload summations ............................. Data Figure Page 19

Body-canard-tail characteristics, main balance and panelload summations ............................. Data Figure Page 91

Page 6: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE
Page 7: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

AERODYNAMICCHARACTERISTICSOFA CANARD-CONTROLLED

MISSILEAT MACHNUMBERSOF 0.8, 1.3, AND1.75

Donald L. Kassner and Brian Wettlaufer*

AmesResearchCenter

SUMMARY

A typical missile model with nose-mountedcanards and cruciform tailsurfaces was tested in the Ames6- by 6-Foot WindTunnel to determine thecontributions of the componentaerodynamic surfaces to the static aero-dynamic characteristics at Machnumbersof 0.8, 1.3, and 1.75 and Reynoldsnumberof 6.25 x 105, based on body diameter. Data were obtained at anglesof attack ranging from 0° to 24° for various stages of model "build-up"(i.e., with and without canard and/or tail surfaces). In addition, twodifferent sets of canards and tail surfaces were investigated.

For the canard and tail arrangements investigated, the model wastrimmable at angles of attack up to about 7° with canard deflections ofabout I0 °. Also, the tail arrangements studied provided ample pitchstability.

INTRODUCTION

Somerecent emphasis in missile technology has been in the area ofdeveloping a series of configurations with canard controls on the non-constant-diameter nose portion of the missile. The objectives have beento provide both terminal guidance and high maneuverability during theflight. Of concern is the influence of the canard-control surfaces on themissile-tail effectiveness caused by the trailing vortices from the canards.Present predictive techniques (e.g., ref. I) have been demonstrated to beinadequate, particularly for the case of the canards located on nonconstant-diameter regions of the missile (e.g., the nose). Accordingly, an exten-sive series of wind-tunnel tests has been performed to provide basic ex-perimental data to be used in developing the required improved predictivetechniques.

This test addressed itself to the determination of the aerodynamiccharacteristics of a typical missile model with and without canards and/or tail surfaces at Machnumbersof 0.8, 1.3, and 1.75. Data were obtained

* Project Engineer, ARO, Inc.

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at angles of attack from 0° to 24° and canard-deflection angles of 0°, 5° ,I0 ° and 15° . Similar data for Machnumbersof 1.5 and 2.0 are presentedin references 2 through 4.

NOMENCLATURE

The axis systems and sign convention are shownin figures 1 and 2.Data are presented in the unrolled body-axis coordinate system. Becausethe data were computer-plotted, the corresponding plot symbol, where used,is given together with the conventional symbol.

PlotSymbol Symbol Defi ni ti on

CA CA missile axial-force coefficient in unrolled body-

axis system; axial force/SREFq _

C_ CBL missile rolling-moment coefficient in unrolled body-

axis system; body rolling moment/SREFq _RE F

C_C(B ) CRMCrolling-moment coefficient in body-axis system forcanard panels summed together

C_C(B)+T(B)CRMBrolling-moment coefficient in body-axis system forall canard and tail panels summed together

C_T(B ) CRMTrolling-moment coefficient in body-axis system fortail panels summed together

Cm CM missile pitching-moment coefficient measured in un-

rolled body-axis system; pitching moment/SREFq _REF

C CMCmC(B)

pitching-moment coefficient in unrolled body-axissystem for canard panels summed together

C CMBmC_B)+T(B)

pitching-moment coefficient in unrolled body-axissystem for all canard and tail panels summed together

C CMTmT(B)

pitching-moment coefficient in unrolled body-axissystem for tail panels summed together

CN CN

BETA

missile normal-force coefficient in unrolled body-

axis system; body normal force/SREFq _

angle of sideslip, deg.

Page 9: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

PlotSymbol Sm_Sy_m_bgl_bo I

CNc(B ) CNC

CNc(B)+T(B)CNB

CNT(B ) CNT

C CYMn

C CYMCnC(B)

C CYMBnC(B)+T(B)

C CYMTnT(B)

Cy CY

CYc(B ) CYC

CYc(B)+T(B) CYB

CYT(B ) CYT

_REF LREF

M MACHOo

Q

SREF SREF

Definition

normal-force coefficient in unrolled body-axis systemfor canard panels summed together

normal-force coefficient in unrolled body-axis systemfor all canard and tail panels summed together

normal-force coefficient in unrolled body-axis systemfor tail panels summed together

missile yawing-moment coefficient in unrolled body-

axis system; bodyyawing moment/SREFq _REF

yawing-moment coefficient in unrolled body-axis systemfor canard panels summed together

yawing-moment coefficient in unrolled body-axis systemfor all canard and tail pane]s summed together

yawing-moment coefficient in unrolled body-axis systemfor tail panels summed together

missile side-force coefficient in unrolled body-axis

system; body side force/SREFq"

side-force coefficient in unrolled body-axis systemfor canard panels summed together

side-force coefficient in unrolled body-axis systemfor all canard and tail panels summed together

side-force coefficient in unrolled body-axis systemfor tail panels summed together

reference length for all coefficients (missile bodydiameter for cylindrical portion); 12.70 cm (0.417 ft)

free-stream Mach number

free-stream dynamic pressure

reference area for all coefficients (cross-sectionalarea of cylindrical portion of center body); 126.7 cm2(0.136 ft Z)

Page 10: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

S_ymbol

Cz

*C

T

6CX

B

C1

C2

C3

C4

C6

C7

N1

N2

N3

T 1

T2

Plot

Symbol

ALPHA

PHI -C

PHI -T

D(X)

B

C1

C2

C3

C4

C6

C7

N1

N2

N3

T1

T2

Definition

angle of attack, deg

missile roll angle, deg

interdigitation anqle between canard and tail panels,deg

Control Surface Code

deflection angle of canard panel number X,(X = l, 2, 3, 4); see figure 2

Configuration Code

body

small canards (aft position)

small canards (mid position)

small canards (forward position)

large canards (mid position)

large canards (aft position)

small canards (mid position)

sharp nose

blunt nose

semiblunt nose

tail panels (aft position)

tail panels (mid position)

Page 11: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

TESTFACILITY

The AmesResearch Center 6- by 6-Foot WindTunnel is a variable-pressure, continuous-flow, closed-return type facility. The nozzle lead-ing to the test section is of the asymmetric sliding-block type whichpermits a continuous variation of Machnumberfrom 0.25 to 2.3. The testsection has a perforated floor and ceiling with provisions for removal ofboundary-layer flow at transonic Machnumbers.

MODELDESCRIPTION

The model and its componentsare shown in figure 3. The model was asting-mounted body of revolution, 12.70 cm in diameter and 132.08 cm inlength, as shownin figure 3(a). Three nose shapes were used: a pointed,three-caliber tangent ogive and two blunted, three-caliber tangent ogives,as shown in figure 3(b). The model used six sets of four canard fins andtwo sets of four tail fins, all with various aspect ratios, as shown infigures 3(c) and 3(d), respectively. The dimensions of the canard andtail fins are given in table I. The locations of the canards and tailson the body are indicated in the nomenclature and figure 3(a). Each ofthe four canards and four tail fins had a three-component balance mountedinside the body. The four tail fins had a fixed incidence angle of 0°.Each canard had a variable incidence angle that was remotely controlledand monitored from outside the tunnel. The tail fins were rolled atangles of 0° and -45° with respect to the canards. The total model loadswere measured on a 5.l-cm (2-in) six-component balance (Task MKIIIE) fur-nished by Ames.

Model photographs are presented in figure 4.

TESTING AND PROCEDURE

The investigation was conducted at Mach numbers of 0.8, 1.3, and1.75 and at a Reynolds number of 6.25 x 105 , based on body diameter. Datawere obtained at angles of attack from 0° to 24 ° and at canard incidenceangles of 0 °, 5° , I0 ° and 15 ° . The experimental data, presented as afunction of angle of attack, were obtained from pitch sweeps at a constantcanard-deflection angle. An angle transducer, mounted on the aft end ofthe model support, was used to measure the angle of attack of the model.

DATA REDUCTION

The six-component main balance forces and moments were corrected forweight tares and reduced to coefficients in the unrolled body-axis system,

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as shownin figure I. The momentreference center for all body-axis coef-ficients was at model station 66 (one-half the length of the sharp-nosedbody in figure 3(a)). All force and momentcoefficients were based uponthe following dimensions:

SREF = 126.7 cm2 (0.136 ft 2)

_REF= 12.70 cm (0.417 ft)

The three-component fin balance forces and momentsfor each canardand tail panel were reduced to normal-force, pitching-moment, and rootbending-momentcoefficients about an axis system in the plane of the fin,as shownin figure 2. These fin coefficients were then summedtogetherin two groups, canards and tails, and reduced to coefficients in an axissystem about the model centerline. They were then further reduced tocoefficients about the momentreference center in the unrolled body-axissystem. Coefficients were obtained for each axis system.

The angle of attack was corrected for flow angularity and sting de-flections. Stream-angle corrections used to correct for flow angularitywere based on data taken during the investigation.

RESULTSANDDISCUSSION

Computer-plotted data of CN, Cm, CA, Cy, Cn, and C_ vs e are presentedin figures 5 through 8. The missile model was at ¢ = 0 for all resultspresented in this report.

Body-Alone Characteristics

Body-alone characteristics for configuration BN3are shownin figure 5for Machnumbersof 0.8, 1.3, and 1.75 and angles of attack from 0° to 24° .As in previous body-alone tests (e.g., ref. 5), CN increases not only with

but with an increase in Machnumberfrom subsonic to supersonic. Theincrease in CN with increase in Machnumberfrom M_,= 0.8 (subsonic) toM_= 1.75 (supersonic) is generally in accord with that which would bepredicted from crossflow theory (refs. 6 and 7) for bodies of revolution.

It is interesting to note that at _ = 0.8, reasonably large side-forceand yawing-momentcoefficients were obtained at angles of attack greaterthan about 19° , even though the body was at zero sideslip (_ = 0°). Unde-sirable side forces and yawing momentshave been shownto accompanytheformation of asymmetric separation and vortex patterns for bodies aloneat subsonic Machnumbers(e.g., ref. 7). Fortunately, the side forces and

Page 13: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

yawing momentsvirtually disappear with increase in Machnumber into thesupersonic regime.

Body-Tail Characteristics

Body-tail characteristics for configuration BN3T2are presented infigure 6 for Machnumbersof 0.8 and 1.75. The circular symbols representthe results for the body with tail (BN3T2) while the square symbols repre-sent the results for the tail alone (summation of four tail panels in thepresence of the body).

Generally, the tail (T2) developed at least half the total CN forup to about 12° . At higher _, the tail becameless effective than the bodyand developed less than half of the total CN for the combination. By com-paring the C_ results of figures 5 and 6, oHe can observe the strong effectof the tail in providing stability in the pitch plane. Also, it can beseen in figure 6 that the Cm vs _ results for the body plus tail are notgreatly different from those for the tail alone.

The side-force and yawing-momentcoefficients for the body plus tailand the tail (in the presence of the body) were generally not large ateither M== 0.8 or 1.75. At M== 0.8, the unwanted side-force and yawing-momentcoefficients measuredfor the body alone at e greater than about 19°(figure 5) were generally less with the tail present (fig. 6)°

Body-CanardCharacteristics

Body-canard characteristics for configuration BN3C6are presented infigure 7 for Machnumbersof 0.8, 1.3, and 1.75. The circular symbolsrepresent the results for the body with canard (BN3C6) while the squaresymbols represent the results for the canard alone (summationof four canardpanels in the presence of the body). Results are presented first for allthe canard panels (position X = I, 2, 3, 4) undeflected, aCX = D(X) = 0°(see fig. 2). Then results are presented for D2 = D4 = 5°. Next, resultsare presented for D2 = D4= I0 °, Finally, results are presented forD2= D4= 15° . In all cases, the vertical panels (at positions I and 3)are undeflected (DI = D3 = 0°).

Generally, the undeflected canard panels (DI = D2 : D3 = D4 = 0° for

C6) developed less than half the total CN at all of the test Mach numbers.Being located well forward of the pitching-moment reference center, the

canard panels also contributed substantially to the unstable pitching-

moment characteristics, typical of the body without tail fins. With changein panel deflection from D2 = D4 = 0° to 15°, the unstable contribution

of the canard panels decreased.

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With addition of the canard panels (C6) to the body (BN3), the unde-sirable side forces and yawing moments for the body at the higher anglesof attack (_ > 19 ° ) were virtually eliminated. (For example, compare Cyresults in figs. 5 and 7.)

Body-Canard-Tail Characteristics

Body-canard-tail characteristics for configurations BN3C7TI andBN3C6T2 are presented in figure 8 for Mach numbers of 0.8, 1.3, and 1.75.The circular symbols represent the results for the body BN3 with canard(C7 or C6) and tail (TI or T2). The square symbols represent the resultsfor the canard alone (summation of four panels in the presence of the body),and the diamond symbols represent the results for the tail alone (summationof four panels in the presence of the body). Finally, the triangularsymbols represent the results for the canard plus tail in the presence ofthe body. As for the body-canard characteristics in figure 7, results arepresented for the side canard panels (at positions 2 and 4) undeflected anddeflected 5° , I0 °, and 15° . The top and bottom canard panels were, ofcourse, always undeflected.

Generally, the canard plus tail (C7TI or C6T2) developed about halfthe total CN for _ up to about 12 ° . At higher _, the body produced themost CN. However, enough normal force was produced by the tail to producestable Cm characteristics over most of the _ range. Also, the canards weregenerally effective in trimming the model (Cm = O) at angles of attack upto about 7° with panel deflections of I0 °. There was little effect on trimangle with further increase in panel deflection to 15° . The reader, ofcourse, can study the various results for each configuration, M_ andcanard deflection angle.

CONCLUDING REMARKS

A typical missile model with nose-mounted canards and cruciform tailsurfaces was tested in the Ames 6- by 6-Foot Wind Tunnel to determine thecontributions of the component aerodynamic surfaces to the static aero-dynamic characteristics at Mach numbers of 0.8, 1.3, and 1.75 and Reynoldsnumber of 6.25 x 105 , based on body diameter. Data were obtained at anglesof attack ranging from 0° to 24 ° for various stages of model "build-up"(i.e., with and without canard and/or tail surfaces). In addition, twodifferent sets of canards and tail surfaces were investigated.

For the canard and tail arrangements investigated, the model wastrimmable at angles of attack up to about 7° with canard deflections ofabout I0 °. Also, the tail arrangements studied provided ample pitchstability.

Page 15: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

AmesResearch CenterNational Aeronautics and Space Administration

Moffett Field, California 94035 April 6, 1977

REFERENCES

I ,

J

.

6

.

.

Pitts, William C.; Nielsen, Jack N.; and Kaattari, George E. : _ftand Center of P_essure of Wind-Body-Tail Combinations at SubsonZc,Transonic and Supersonic Speeds. NACA Rep. 1307, 1957.

Kassner, DonaZd L.; and Wettlaufer, Brian" Aerodynamic Character-istics of a Canard-Controlled M_'_s_le at Math Numbe_ of I. 5 and2.0. NASA TM X-73,219, 1977.

Kassner, Donald L.; and Wettlaufer, Brian: Effect_ of CanardLocation on The A_odynamic Characteristics of a Blunt-NosedMissile at Mach Numbers of 1.5 and 2.0. NASA TM X-73,220, 1977.

Kassner, Donald L.; and Wettlaufer, Brian: Effects of Canard Loca-tion on the Aerodynamic Characteristics of a Sharp-Nosed Missileat Mach Numbers of 1.5 and 2.0. NASA TM X-73,221, 1977.

Jorgensen, Leland H.; and Nelson, Edgar R.: Experimental AerodynamicCharacteAistics for a Cylindrical Body of Revolution With VarZousNoses at Angles of Attack From 0 ° to 58 ° and Maeh Numbers From 0.6to 2.0. NASA TM X-3128, 1974.

Jorgensen, Let_d H. : Prediction of Static Aerodynamic Character-istics for Space Shuttle-_ke and Other Bodies at Angles of At.tackfrom 0 ° to 180 ° . NASA TN D-6996, 1973.

Jorgensen, Leland H. : PredZc_Lon of Static Aerodynamic Character-istics for SZender Bodies A_one and With Llfting Sl_face_ to VeryHigh Angles of Attack. NASA TM X-73,123, 1976.

Page 16: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

TABLE I. - DIMENSIONS OF CONTROL PANELSa

C1 C2 C3 C4 C6 C7 T 1 T 2

45

1.68 1.68 1.68 2.40 2.54

5.08 5.08 5.08 7.18 10,16

.25 .25 .25 .36 .38

3.81 3.81 3.81 5.39 9.53

2.11 2.11 2.11 2.98 4.37

.08 .08 .08 .08 .15

0 0 0 0 0

1.52 1.52 1.52 2.15

0 0 0 0 0

1.68 1.68 1.68 2.40 2.54

2.37

7.18

.36

3 56

2 98

17

81

3 84

81

7.37

0 45

3.18 3.81

12.70 17.78

.51 ,51

6.35 8.89

5.72 7.62

.51 .51

3.18 3.81

12.70 8.89

aNote- all dimensions are in centimeters except "A",which is in degrees.

See control panel drawing, fig. 3(c).

I0

Page 17: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

I']I,(

V ilil'_l

C ,

i III

{'

NOt'B: POSITIVE DIRECTIONS OF FORCE

COEFFICIENTS, MOMENT COEFFI-

CIE_S_ AND ANGLES ARE INDI-

CATED BY ARROWS.

FIGURE I. - Axis System.

]I

Page 18: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

, "IIC]L .._-

I

:I

'lqT ]

i

i

Cp 4-

C_Ir,,X

k.J (, _f

-- _'['X

'I'A [_1;'

Figure 2. - Control panels sign convention.

12

Page 19: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

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Page 20: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

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Page 21: i NASA TECHNICAL NASA TM X-73,218 MEMORANDUM · 2013-08-31 · i NASA TECHNICAL MEMORANDUM NASA TM X-73,218 00 oq:E I--¢/3 z AERODYNAMIC CHARACTERISTICS OF A CANARD-CONTROLLED MISSILE

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