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EXAMINATION OF RECENT LATERAL - STABILITY-DERIVATIVE DATA Frank S. Malvestuto, Jr., and Richard E. Kuhn Langley Aeronautical Laboratory Langley Fie l d, Va.
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NAT IONAL AD VISORY CO MMITTEE
F OR A ERONA UTICS
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NACA RM L73108a NATIONAL ADVISORY COl4WJTEZ FOR AERONAUTICS RESEARCH MEMORANDUM EXAMINATION OF RECENT I.ATERAL-STABILITY-DEBIVkTIVE DATA By Frank S . Malvestuto, Jr., and Richard E . K u h n INTRODUCTION In the present paper attention is directed to the aerodynamic parameters, the so-called stability derivatives, that affect the lateral behavior of airplanes and missiles. The discussion is centered on three
important quantities Czp, the effective-dihedral derivative, k,, the
directional-stability derivative, and Cz , the damping-in-roll deriva-
P tive. These quantities are considered for a large angle-of-attack range at subsonic speeds. A few remarks will also be made on the sideslip derivatives at zero lift in the supersonic speed range.
DISCUSSION For the subsonic speed range, the lateral-stability derivatives have been the subject of intensive research by the Langley high-speed 7 - by 10-foot tunnel. Particular attention has been paid to the varia- tion with Mach number in the high angle-of-attack range that is repre- sentative of flyable attitudes of .manyhigh-speed airplanes. The effective-dihedral and the directional-stability derivatives of the three complete models sketched in figure 1 are presented in figures 2 and 3 . Model I is equipped with a 300 sweptback wing of aspect ratio 3; model I1 has a 450 swept wing of aspect ratio 4; and model I11 (repre- senting the X-3 airplane) is equipped with a 60° swept wing of aspect ratio 2 . To the right of each sketch in figure 1 is a plot of the model lift coefficient against angle of attack for two available Mach numbers indicative of the low and high subsonic speed range.
The effective-dihedral derivative C z p , expressed here in radians, for the three models is presented in figure 2 for the range of angle of attack and the Yach numbers indicated in figure 1. It is important to note the highly nonlinear variation of this derivative with angle of attack and the pronounced effect of Mach number on these variations.
upon the separation of This nonlinear behavior is strongly dependent flow from the wings, particularly in the vicinity of the tips, and .e e.. e.. e e. e. . . . e.. e.
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2 e.. e. NACA RM ~33108a % commences a t angles of attack a t which these swept wings a r e by no means completely s t a l l e d . Note t h a t model I retains i t s positive effective dihedral t h a t is, through the angle-of-attack range and increasing
-czP) (
Mach number tended t o increase this quantity a t the higher angles.
Models I1 and I11 have the more t y p i c a l variation of C with angle of 2 P attack and show the decrease t o zero and t o negative effective dihedral a t the higher angles. Configurations having t h i s l a t t e r type of varia- t i o n of C z and the derivative CnP, t o be discussed l a t e r , could P be f l y i n g a t angles a t which one or the other of these deriva- easily tives becomes zero. These zero values of the derivatives could seriously a f f e c t the l a t e r a l behavior of airplanes a t these higher angles of attack.
The point t o be observed from the data presented here is t h a t increasing Mach number may change the angle of attack a t which these derivatives become zero. A s an i l l u s t r a t i o n , the r e s u l t s of model I1 show t h a t become increasing Mach number increases the angle a t which c 2 8 and CnP zero; whereas, f o r model 111, the Mach number e f f e c t i s reversed; t h a t is, increasing Mach number decreases the angle of attack a t which zero values occur.
The e f f e c t s of angle of attack and Mach number on the companion derivative are sham i n figure 3 . A t the higher angles the varia- CnP t i o n of t h i s derivative depends not only upon the t a i l effectiveness, that is, the difference between the tail-on and t a i l - o f f r e s u l t s , but a l s o may be greatly influenced by the variation of the ving-body charac- t e r i s t i c s . As an example, f o r models I and I1 the increase i n the sta- b i l i t y of the wing-body combination a t the higher Mach number tends t o compensate f o r the reduction i n t a i l effectiveness s h a m by the decrease i n the increment between the tail-on and t a i l - o f f r e s u l t s . For model 111, however, although the t a i l effectiveness remains appreciably constant up t o large angles of attack, the decrease i n the s t a b i l i t y of the wing-body a reduction i n Cn f o r the complete model and i s the combination causes P primary cause of t h i s reduction. It i s also of i n t e r e s t t o point out f o r t h i s model t h a t the angle of attack a t which C z and C , tend t o zero P P i s approximately the same and decreases with increasing Mach number. T h i s similarity of the action of Mach number on C and Cn i s not surprising P since f o r this model the wing-body characteristics, which i n the main usu- a l l y control C are also the controlling influence f o r Cn as w a s l P 9 P indicated previously. These r e s u l t s emphasize the need f o r having, through the Mach range, not only proper t a i l effectiveness, but equally important, proper wing-body design, incorporating satisfactory directional characteristics.
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0 . 0 0 0 0 0 0 0 NACA RM L53I08a 0 0 0.0 The e f f e c t s of horizontal-tail height on the d i r e c t i o n a l - s t a b i l i t y derivative Cn and a l s o on the effective-dihedral derivative C f o r P model I are shown i n figures 4 and 5 . The curves on the l e f t of each figure represent horizontal-tail-off data.; the next set of curves are f o r tne horizontal t a i l i n the low position. This arrangement i s t'ne one con- sidered i n the previous figures. The data t o the r i g h t are f o r the hori- zontal t a i l i n high position. The expected increase i n the directional- s t a b i l i t y derivative with the t a i l i n the high position i s c l e a r l y evident from these results. For the effective-dihedral derivative C the r e l o - IP , cation of the t a i l from the low t o the high position produced again, as expected, an increase i n the negative value of the derivative.
There is one additional point related t o the s i d e s l i p derivatives devise "opthum f i x e s " t o t h a t deserves consideration. In attempts t o a l l e v i a t e the pitch-up conditions f o r various airplanes, consideration has a l s o been given t o the e f f e c t of these same f i x e s on the lateral derivatives. The r e s u l t s available so far are very limited and no spec- i f i c conclusion can be made. The data of figure 6, however, illustrate f o r one configuration, model 111, the e f f e c t of a leading-edge chord- extension on the Cn and C z p derivatives. A t the lower Mach number P the e f f e c t of chord-extensions i n producing a l i n e a r pitching-moment variation i s clearly evident, but the e f f e c t of these chord-extensions on the corresponding Cn and C derivatives are r e l a t i v e l y insignif- P IP icant. A t the higher Mach number, although unfortunately the available chord-extension-on data are somewhat incomplete, the small e f f e c t of these chord-extensions on the derivatives i s s t i l l evident, the trend f o r the higher Mach number being almost i d e n t i c a l t o t h a t shown f o r the lower Mach number. It should be remembered, of course, that C 2 d i d not show P any pronounced breaks u n t i l angles of attack approaching stall were reached.
So far, the discussion of the lateral derivatives f o r the subsonic speed range has been directed toward the s t a t i c e f f e c t s . Recently, the characteristics i n steady r o l l of several wings a t high angles of attack For i n the subsonic speed range have been investigated experimentally.
a 4 5 O swept-wing-body arrangement, the variation of the damping-in-roll parameter C with angle of attack and Mach number is shown i n figure 7, IP together with the corresponding l i f t variations. It can be seen that a t a Mach number of 0.2 the wing maintains a reasonable amount of damping a t all angles of attack up t o the stall. However, as the Mach number i s increased, the damping-in-roll a b i l i t y of the wing seriously diminishes u n t i l at a Mach number of 0.91 i n s t a b i l i t y i n roll is indicated a t an angle of attack of 11'. Note also that t h i s e f f e c t occurs although the l i f t is s t i l l increasing a t this angle of attack. Similar e f f e c t s occur f o r wings of other plan forms as indicated i n figure 8. It w i l l be nGted * here that a l l these wings indicate a serious l o s s i n damping effectiveness that, with the excep- i n about the same angle-of-attack range. Note a l s o c this loss occurs although the over-all l i f t t i o n of the unswept wing, coefficients of the wings are s t i l l increasing. For t h e unswept wing, t h i s l o s s i n damping occurs a t angles of attack corresponding t o the stall, as would be expected.
One additional important point connected w i t h these regions of poor damping i s t h a t the variation of r o l l i n g moment with r o l l i n g velocity may be very irregular as shown i n figure 9. Under these conditions it i s d i f f i c u l t t o determine a representative value of the damping coefficient.
The data shown i n figure 9 are f o r a Mach number of 0.85. The variation of the rolling-moment coefficient with r o l l i n g velocity shown by the dashed curve is representative of the l i n e a r s t a b l e slope characteristic of the A t a n angle of attack of 1l0, however, the vari- low angle-of-attack range.
a t i o n i s nonlinear and, i n the case of the 32.6' swept wing, it is unstable l over a very wide range of pb/2V. The hysteresis shown i n the data f o r the unswept wing and t h e 60° triangular wing would certainly give r i s e t o some undesirable dynamic-stability characteristics and possibly complicate the The i n s t a b i l i t y a t sma,l1 design of any automatic s t a b i l i z i n g equipment.
values of pb/2V and the associated hysteresis loops a l s o may have some relationship t o the wing-dropping problem.
Some consideration has been given t o the use of f i x e s i n an attempt Since a loss i n daurping i s asso- t o reduce the l o s s of damping i n r o l l .
ciated w i t h t i p s t a l l i n g , which i s also a contributing f a c t o r i n producing pitch-up, tests were made t o determine whether devices which a r e known t o a l l e v i a t e pitch-up would also improve the damping i n r o l l . The e f f e c t of l a fence on the dmrping characteristics of the 4 5 O swept w i r a i s shown i n figure 10. 0.65 b/2 The fences were f u l l chord and were located a t the s t a t i o n . For the Mach number of 0.85, the fences delayed the pitch-up by some 5 O and decidedly improved the damping. A t aMach number of 0.91, however, the e f f e c t of the fences on e i t h e r the damping o r the pitch-up decreased considerably. Reference 1 contains a more complete discussion of the damping-in-roll characteristics of swept wings a t high angles of attack and high subsonic speeds. Included also i n this report is a simple procedure f o r estimating the load d i s t r i b u t i o n i n r o l l provided the corres- ponding angle-of-attack load d i s t r i b u t i o n i s known.
The preceding discussion of the l a t e r a l - s t a b i l i t y derivatives a t high angles of attack has of necessity been based wholly on experimental data.
This discussion has been confined t o the subsonic speed range.
In the supersonic speed range, recent t h e o r e t i c a l work applied t o three complete configurations has demonstrated the a b i l i t y of theory t o predict the l a t e r a l - s t a b i l i t y derivatives a t low angles of attack. The variations of the derivatives C and Cn with Mach number f o r these three IP P configurations a r e shown i n figures 1 1 and 12. The theoretical r e s u l t s are presented for the complete arrangement, v e r t i c a l - t a i l alone, and body o r wing-body alone. The experimental r e s u l t s , the dark c i r c l e s , are f o r The comparison of theory and experiment indi- the complete arrangement.
cates that the l e v e l and trend of the experimental variations a r e pre- dicted by the theory. For one of these airplanes a thorough study and prediction of all the major longitudinal and l a t e r a l derivatives has been made and is reported i n reference 2.
CONCLUDING REMARKS It has not been possible t o consider a l l the recent infomation on l a t e r a l - s t a b i l i t y derivatives. However, a bibliography of papers con- taining lateral-stability-derivative data has been attached. Reference 3 contains a large number of references not included here. The f o l - a l s o lowing remarks are offered as an indication of the present general status of the stability-derivative field.
A t l o w angles of attack within the subsonic speed range below the c r i t i c a l Mach number, it is f e l t that available theory permits fairly r e l i a b l e predictions of t h e l a t e r a l - s t a b i l i t y derivatives.
A t the higher angles of attack i n the subsonic and transonic ranges, the unpredictable, nonlinear characteristics of the derivatives stress the necessity f o r determining experimentally f o r a p a r t i c u l a r configura- t i o n the derivatives needed i n the estimation of s t a b i l i t y .
In the supersonic range a t low angles of attack, combined t h e o r e t i c a l and experimental studies have produced useful aerodynamic-derivative data.
For the complete configurations so far considered, derivative estimates made f o r these conditions have m e t with a good measure of success.
I n t h e supersonic range a t high angles of attack there are no data available.
Langley Aeronautical Laboratory, National Advisory Committee for Aeronautics, Langley Field, Va., A u g u s t 26, 1933.
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6 0 0 0 0 . NACA RM L53108a REFERENCES Notes on Damping i n Roll and Load Distributions 1. Kuhn, Richard E.: NACA i n Roll a t High Angles of Attack and High Subsonic Speed.
2. Margolis, Kenneth, and Bobbitt, Percy J.: Theoretical Calculations of the S t a b i l i t y Derivatives a t Supersonic Speeds f o r a High-speed Airplane Configuration. NACA RM L53G17, 1953 Summary of Methods f o r 3. Campbell, John P., and McKinney, Marion 0.: Calculating Dynamic Lateral S t a b i l i t y and Response and f o r Estimating Lateral S t a b i l i t y Derivatives. NACA Rep. 1098, 1952. (Supersedes NACA TN 2409. ) BIBLIOGRAPHY THEORETICAL STUDIES AND ESTIMATING PROCEDURES 4. Purser, Paul E.: An Approximation t o the Effect of Geometric Dihedral on the Rolling Moment Due t o Sideslip f o r Wings a t Transonic and Supersonic Speeds. NACA RM L52BOl, 1952.
5. Margolis, Kenneth, Sherman, Windsor L., and Hannah, Margery E.: Theo- r e t i c a l Calculation of the Pressure Distribution, Span Loading, and Rolling Moment Due t o Sideslip a t Supersonic Speeds f o r Thin Sweptback Tapered W i n g s With Supersonic Trailing Edges and Wing Tips Parallel t o the Axis of Wing Symmetry. NACA TN 2898, 1973.
The Aerodynamic Derivatives With 6. Robinson, A , , and Hunter-Tod, J. H.: Respect t o Sideslip f o r a Delta Wing With Small Dihedral a t Supersonic Speeds. Rep. No. 12, College of Aero., Cranfield ( B r i t i s h ) , Dec. 1947.
Theoretical S t a b i l i t y Derivatives of a Highly Swept Delta 7. Nonweiler, T.: Wing and Slender Body Combination. Rep. No. 50, College of Aero., Cranfield (British), Nov. 1951.
L i f t and Moment Changes Due t o the Fuselage f o r a Yawed 8. Jacobs, W i l l i : Aeroplane With Unswept and Swept Wings. Rep No. 34, Aero. R e s . I n s t .
of Sweden (Stockholm), 1950.
9. Ksoll,-R.: Theoretical Investigations on the Rolling Moment Due t o Side S l i p of Wing and Fuselage Arrangements With a Fuselage of Pear Shaped Cross Section. Reps. and Translations No. 134, B r i t i s h .
10. Martin, John C . , and Malvestuto, Frank S., Jr.: Theoretical Force and Moments Due t o Sideslip of a Number of Vertical T a i l Configurations a t Supersonic Speeds. NACA T N 2412, 1951.
11. Rileyz Donald R.: Effect of Horizontal-Tail S p a n and Vertical Lncn_t.lon on the Aerodynamic Characteristics of an Unswept T a i l Assembly i n Sideslip. NACA T N 2907, 1953.
12. Coale, Charles W.: Restoring Moment i n Yaw Due t o Interference Between Rep.
t h e Vertical Stabilizer and Fuselage a t Supersonic Velocities.
N o . SM-13496, Douglas Aircraft Co., Inc., Feb. 7, 1949.
13. Owen, P. R . , and Andersen, R. G.: Interference Between the Wings and t h e T a i l Surfaces of a Cornbination of Slender Body, Cruciform Wings and Cruciform T a i l Set a t Both Incidence and Yaw. Rep. No. Aero. 2471, B r i t i s h R.A.E., June 1952.
Directional S t a b i l i t y Characteristics 14. Tscherfinger, W., and Decker, J. L.: of Tee-Tails. Eng. Rep. No. 4797, The Glenn L. Martin Co., Feb. 20, 1952.
15. Falkner, V. M.: R o t a r y Derivatives i n Yaw. Aircraft Engineering, vol. XXIII, no. 264, Feb. 1951, pp. 44-50, 54.
16. Hunter-Tod, J. H.: The Aerodynamic Derivatives With Respect t o R a t e of Yaw f o r a Delta Wing With Small Dihedral a t Supersonic Speeds. Rep.
N o . 28, College of Aero., Cranfield ( B r i t i s h ) , March 1949.
17. Ribner, Herbert S.: O n the Effect of Subsonic Trailing Edges on Damping i n Roll and Pitch of Thin Sweptback W i n g s i n a Supersonic Stream. NACA TN 2146, 1950.
Damping i n R o l l of Cruciform and Some Related Delta 18. Ribner, Herbert S.: W i n g s a t Supersonic Speeds. NACA TN 2285, 1951.
Method f o r Calculating the Rolling and Y a w i n g Moments 19. Martina, Albert P.: Due t o Rolling f o r Unswept Wings With o r Without Flaps o r Ailerons by Use of Nonlinear Section L i f t Data. NACA TN 2937, 1953.
A Simple Approximate Method f o r Calculating Span- 20. Diederich, Franklin W.: wise L i f t Distributions and Aerodynamic Influence Coefficients at Sub- sonic Speeds. NACA TN 2751, 1952.
21. Diederich, Franklin W., and Zlotnick, Martin: Theoretical Spanwise L i f t at Speeds Below and Above the Distributions of Low-Aspect-Ratio W i n g s Speed of Sound. NACA TN 1973, 1949.
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A Plan-Form Parameter f o r Correlating Certain 22. Diederich, Franklin W . : Aerodynamic Characteristics of Swept Wings. NACA TN 2335, 1951.
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23. DeYoung, John: Theoretical Antisymmetric Span Loading f o r Wings of Arbitrary Plan Form a t Subsonic Speeds. NACA Rep. 1056, 1951.
(Supersedes NACA TN 2140.)
24. Moeckel, W . E., and W a r d , J. C.: Load Distributions Due t o Steady NACA TN 1689, Roll and Pitch f o r Thin Wings a t Supersonic Speeds.
1948.
25. Bleviss, Zegmund 0.: Some Roll Characteristics of Cruciform Delta Wings a t Supersonic Speeds. Jour. Aero. Sci., vol. 18, no. 5, May 1951, PP. 289-297.
Some Roll Characteristics of Plane and Cruciform 26. Bleviss, Zegmund 0.: Delta Ailerons and Wings i n Supersonic Flow. Rep. No. SM-13431, Douglas Aircraft Co., Inc., June 1949.
27. Lagerstrom, P. A . , and G r a h a m , Martha E.: Some Aerodynamic Formulas i n Linearized Supersonic Theory f o r Damping i n Roll and Effect of Twist for Trapezoidal Wings. Rep. No. SM-13200, Douglas Aircraft Co., Inc., March 12, 1948.
28. Graham, Ernest W . : A Limiting Case f o r Missile Rolling Moments. Jour.
Aero. Sci., vol. 18, no. 9, Sept. 1951, pp. 624-628.
29. Miles, John W . : A Note on the Damping i n Roll of a Cruciform Winged Body. Quarterly Appl. Math., vol. X, no. 3 , Oct. 1952, pp. 276-277.
30. Adam, Gaynor J., and Dugan, Duane W . : Theoretical Damping i n Roll and Rolling Moment Due t o Differential Wing Incidence f o r Slender Cruciform Wings and Wing-Body Combinations. NACA Rep. 1088, 1952.
31. Van Meter, J. T.: Damping i n Roll of Triangular Planform Wings i n Super- Meteor Rep. UAC-34, United Aircraft Corp., June 1949.
sonic Flow.
32. Lehrian, Doris E.: Calculation of the Damping f o r Rolling Oscillations of a Swept Wing. C . P. No. 51, B r i t i s h N.P.L. (Tech. Rep. 13,448, A . R . C . ) , 1951.
33. Bobbitt, Percy J., and Malvestuto, Frank S . , Jr.: Estimation of Forces and Moments Due t o Rolling f o r Several Slender-Tail Configurations a t Supersonic Speeds. NACA TN 2955, 1953.
34. Martin, John C . , and Gerber, Nathan: O n the Effect of Thickness on the Damping i n Roll of A i r f o i l s a t Supersonic Speeds. Rep. N o . 843, B a l l i s t i c Res. Labs., Aberdeen Voving Ground, Jan. 1953.
0.. . . . 0 .
NACA RM L53108a
- 35. Nicolaides, John D., and Bolz, Ray E . : On the Pure Rolling Motion of
Winged and/or Finned Missiles in Varying Supersonic Flight. Rep.
No. 799, Ballistic Res. Labs., Aberdeen Proving Ground, March 1952.
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Wing-Body Interference Effects on the Tail Con- 36. Steinnetz, Harold F.: tribution to the Damping-in-Roll of Supersonic Missiles. Preprint No. 384, S.M.F. Fund Paper, Inst. Aero. Sci.
Wing and Wing-Fuselage Data 3 7 . Letko, William, and Wolhart, Walter D . : Effect of Sweepback on the Low-Speed Static and Rolling Stability Derivatives of Thin Tapered Wings of Aspect Ratio 4 . NACA RM LgF14, 1949.
38. Brewer, Jack D., and Fisher, Lewis R . : Effect of Taper Ratio on the Low-Speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2.61. NACA TN 2555, 1951. (Supersedes NACA RM ~8~18.)
39. Letko, William, and Jaquet, Byron M . : Effect of Airfoil Profile of Symmetrical Sections on the Low-Speed Static-Stability and Yawing Derivatives of 4 5 ' Sweptback Wing Models of Aspect Ratio 2.61.
NACA RM L8Hl0, 1 9 4 8 .
4 0 . Jacquet, Byron M., and Brewer, Jack D.: Low-Speed Static-Stability and Rolling Characteristics of Low-Aspect-Ratio Wings of Triangular and Modified Triangular Plan Forms. NACA RM L8L29, 1949.
41. N e m r k , S.: Lateral Characteristics of Wings of Small Aspect Ratio From Some German Model Tests. Tech. Note No. Aero. 1917, British R.A.E., Sept. 1947.
42. Wolhart, Walter D.: Wind-Tunnel Investigation at Low Speed of the Effects of Symmetrical Deflection of Half-Delta Tip Controls on the Damping in Roll and Yawing Moment Due to Rolling of a Triangular-Wing Model. NACA RM L5lBO9, 1951.
43. Lichtenstein, Jacob H.: Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45O Sweptback Wing. NACA TN 2689, 1952. (Supersedes NACA RM L8G20.)
4 4 . Lichtenstein, Jacob H., and Williams, James L.: Effect of High-Lift Devices on the Static-Lateral-Stability Derivatives of a 45O Sweptback Wing of Aspect Ratio 4 . 0 and Taper Ratio 0 . 6 in Combination With a Body.
NACA TN 2819. 1952.
4 5 . Fisher, Lewis R. : Low-Speed Static Longitudinal and Lateral Stability .
Characteristics of Two Low-Aspect-Ratio Wings Cambered and Twisted To NACA RM L'jlC20, Provide a Uniform Load at a Supersonic Flight Condition.
1 9 5 1 - * Yaw Characteristics and Side- 46. Salmi, Reino J., and Fitzpatrick, James E.: wash Angles of a 42O Sweptback Circular-Arc Wing With a Fuselage and With Leading-Edge and Split Flaps at a Reynolds Number of 5,300,000.
NACA RM L7130, 1947.
47. Salmi, Reino J.: Yaw Characteristics of a 5 2 ' Sweptback Wing of NACA 641-112 Section With a Fuselage and With Leading-Edge and Split NACA Flaps at Reynolds Numbers From 1.93 x lo6 to 6.00 x lo6.
RM ~ 8 ~ 1 2 , 1948.
Aerodynamic Study of a 48. McCormack, Gerald M., and Walling, Walter C . : Wing-Fuselage Combination Employing a Wing Swept Back 630. Investi- gation of a Large-Scale Model at Low Speed.
NACA RM A8D02, 1949.
Measurements of the Damping in Roll 49. Hunton, Lynn W., and Dew, Joseph K.: of Large-Scale Swept-Forward and Swept-Back Wings. NACA RM Apll, 1947.
50. Cole, Henry A., Jr., and Ganzer, Victor M.: Experimental Investigation of Rolling Performance of Straight and Sweptback Flexible Wings With Various Ailerons. NACA TN 2563, 1951.
31. Adler, Alfred A.: A Correlation of Theory With Experiment for Low- Aspect-Ratio Wings at Subsonic Speeds. Rep. No. AF-743-A-4 (Air Res.
and Dev. Command Contract No. AF 33(038)-17397 E.O. No. 460-31-12-12 SR lg), Cornell Aero. Lab'., Inc., Dec. 1952.
52. Thiel, G.: Rolling Balance Measurements. Part I1 - Results of Tests
on Two Tapered Wings. British Ministry of Supply Translation No. GDC 1 0 / 4 5 1 ( 11)T (R.A.E. Library Trans. 379, pt. 2), Sept . 1951.
53. Halliday, A. S., Cox, D. K . , and Skelton, W. C.: Measurement of Rolling Moment on an Elliptic Wing on the N.P.L. Whirling Arm.
Rep. 10,935, British A.R.C. (S. & C. 2161), Oct. 16, 1947.
Halliday, A. S., and Cox, D. K.: The Measurement of Yawing Moment on 5 4 .
an Elliptic Wing on the Whirling Arm. Rep. 12,497, British A.R.C.
(S. & C. 232O), Aug. 2, 1949.
55. K u h n , Richard E., and Fournier, Paul G . : Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Com- binations at High Subsonic Speeds. Sweep Series. NACA RM L5Xlla,
1952 -
Wind-Tunnel Investigation 5 6 . Fournier, Paul G., and Byrnes, Andrew L., Jr .: of the Static Lateral Stability Characteristics of Wing-Fuselage Com- binations at High Subsonic Speeds. Aspect-Ratio Series. NACA RM ~5x18, 1953 * 5 7 . Wiggins, James W., and Fournier, Paul G. : Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combina- tions at High Subsonic Speeds. Taper-Ratio Series. NACA RM L53B25a, 58. Wiggins, James W.: Wind-Tunnel Investigation at High Subsonic Speeds of the Static-Longitudinal and Static-Lateral Stability Characteristics of a Wing-Fuselage Combination Having a Triangular Wing of Aspect Ratio 2.31 and an NACA 63A00j Airfoil.
NACA RM L53GOga, 1953.
5 9 . Fournier, Paul G.: Wind-Tunnel Investigation of the Aerodynamic Char- acteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing- Fuselage Combination Having a Triangular Wing of Aspect Ratio 4.
NACA RM L53Glba, 1953.
6 0 . K u h n , Richard E., and Draper, John W.: Wind-Tunnel Investigation of the Effects of Geometric Dihedral on the Aerodynamic Characteristics in Pitch and Sideslip of an Unswept- and a 4 5 ' Sweptback-Wing-Fuselage Combination at High Subsonic Speeds. NACA RM L53F09, 1953.
6 1 . Johnson, Harold S . : Wind-Tunnel Investigation at Low Transonic Speeds
of the Effects of Number of Wings on the Lateral-Control Effectiveness of an RM-5 Test Vehicle. NACA RM ~ 9 ~ 1 6 , 1949.
62. Lockwood, Vernard E. : Damping-in-Roll Characteristics of a 42.7O Swept- back Wing As Determined From a Wind-Tunnel Investigation of a Twisted Semispan Wing. NACA RM L9F15, 1949.
6 3 . Lockwood, Vernard E.: Effects of Sweep on the Damping-in-Roll Char- acteristics of Three Sweptback Wings Having an Aspect Ratio of 4 at Transonic Speeds. NACA RM L50Jl9, 1950.
K u h n , Richard E., and Myers, Boyd C., 11: The Effect of Tip Tanks on 6 4 .
the Rolling Characteristics at High Subsonic Mach Nunibers of a Wing Raving an Pspect Ratio of 3 With Quarter-Chord Line Swept Back 35O.
NACA RM LgJlg, 1950.
High-Subsonic Damping-in-Roll 65. Myers, Boyd C., 11, and K u h n , Richard E . : characteristics of a Wing With the Quarter-Chord Line Swept Back 350 NACA RM LgC23, 1 9 4 9 . and With Aspect Ratio 3 and Taper Ratio 0.6.
Effects of Mach Number and 6 6 . K u h n , Richard E., and Myers, Boyd C., 1 1 : Sweep on the Damping-in-Roll Characteristics of Wings of Aspect Ratio 4.
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I 2 NACA F M L53108a A Collection of Data f o r Zero-Lift Damping i n Roll 67. Stone, David G.: of Wing-Body Combinations A s Determined With Rocket-Powered Models Equipped With Roll-Torque Nozzles. NACA RM L53E26, 1953.
Some Effects of Fuselage 68. Bland, W i l l i a m M . , Jr., and D i e t z , Albert E.: Interference, Wing Interference, and Sweepback on the Damping i n Roll of Untapered Wings A s Determined by Techniques Employing Rocket- Propelled Vehicles. NACA RM L5ID25, 1951.
69. Sanders, E. Claude, Jr., and EdmOndson, James L.: Damping i n Roll of Rocket-Powered Test Vehicles Having Swept, Tapered Wings of Low Aspect Ratio. NACA RM ~ 5 1 ~ 0 6 , 1951.
Damping i n Roll of Straight and 45' Swept Wings 70. Sanders, E. Claude, Jr.: of Various Taper Ratios Determined a t High Subsonic, Transonic, and Supersonic Speeds With Rocket-Powered Models. NACA RM L5lHl4, 1951.
Damping i n Roll of Models With 4 5 O , 60°, and 71. Sanders, E. Claude, Jr.: TO0 Delta Wings Determined at High Subsonic, Transonic, and Supersonic Speeds With Rocket-Powered Models. NACA RM L52D22a, 1952.
72. Edmondson, James L.: Damping i n Roll of Rectangular Wings of Several Aspect Ratios and NACA 65A-Series A i r f o i l Sections of Several Thickness Ratios a t Transonic and Supersonic Speeds A s Determined With Rocket- Powered Models. NACA RM ~ 5 0 ~ 2 6 , 1950.
73. Stone, David G . , and Sandahl, C a r l A . : A Comparison of Two Techniques Utilizing Rocket-Propelled Vehicles f o r the Determination of the Damping-in-Roll Derivative. NACA RM ~ 5 1 ~ 1 6 , 1951.
74. Edmondson, James L., and Sanders, E . Claude, Jr.: A Free-Flight Technique f o r Measuring Damping i n Roll by Use of Rocket-Powered Models and Some NACA RM L9101, 1949.
I n i t i a l Results f o r Rectangular Wings.
75. Dietz, Albert E . , and Edmondson, James L.: The Damping i n Roll of Rocket- Powered Test Vehicles Having Rectangular W i n g s With NACA 65-006 and Symmetrical Double-Wedge A i r f o i l Sections of Aspect Ratio 4.5. NACA RM ~ 5 0 ~ 1 0 , 1950.
76. Bland, W i l l i a m M., Jr., and Sandahl, C a r l A . : A Technique Utilizing Rocket Propelled Test Vehicles f o r the Measurement of the Damping i n Roll of Sting-Mounted Models and Some I n i t i a l Results for Delta and Unswept Tapered Wings. NACA RM L50D24, 1950.
77. Hopko, Russell N.: A Flight Investigation of t h e Damping i n Roll and Rolling Effectiveness Including Aeroelastic Effects of Rocket-Propelled Missile Models Having Cruciform, Triangular, Interdigitated Wings and Tails. NACA RM ~ 5 1 ~ 1 6 , 1951.
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NACA RM L53108a ..
Rolling Effectiveness of All- 7 8 . Strass, H. Kurt, and Marley, Edward T.: Movable Wings at Small Angles of Incidence at Mach N d e r s From 0.6 to 1.6.
NACA RM L5lH03, 1951.
79. Bland, William M. Jr.: Effect of Fbelage hterference cii the Daiir3 in Roll of Delta Wings of Aspect Ratio 4 in the Mach Number Range 0.6 and 1 . 6 As Determined With Rocket-Propelled Vehicles.
Between RM L ' j 2 E l 3 , 1952.
NACA Flight Investigation at Sub- 8 0 . Elartz, C. William, and Church, James D.: Transonic, and Supersonic Velocities of the Hinge-Moment Char- sonic, acteristics, Lateral-Control Effectiveness, and Wing Damping in Roll NACA of a 60' Sweptback Delta Wing With Half-Delta Tip Ailerons.
RM ~51~18, 1951.
8 1 . Brown, Clinton E., and Heinke, Harry S., Jr.: Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92. NACA RM L8L30, 1 9 4 9 .
8 2 . McDearmon, Russell W., and Heinke, Harry S . , Jr.: Investigation of the Damping in Roll of Swept and Wpered Wings at Supersonic Speeds. NACA RM L53A13, 1953.
8 3 . Chubb, Robert S.: Experimental Investigation of the Static Aerodynamic and Dynamic Damping-in-Roll Characteristics of an 8-CM Aircraft Rocket With Solid and Slotted Fins. NACA RM A52C04, 1952.
84. Speasman, M. Leroy, and Hilton, John H., Jr.: Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Aspect Ratio of 3.5 and a Taper Ratio of 0.2. Effects of Sweep Angle and Thickness Ratio on the Static Lateral Stability Characteristics at M = 1.60. NACA RM L5lKl5a, 1952.
8 5 . Hamilton, Clyde V . : Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-Body Combinations Having Cambered Wings With an Effects of Sweep Angle Aspect Ratio of 3.5 and a Taper Ratio of 0.2.
and Thickness Ratio on the Static Lateral Stability Characteristics at M = 2.01. NACA RM L52E23, 1952.
Aerodynamic Study of a Wing-Fuselage Combination 8 6 . Lessing, Henry C . :
Employing a Wing Swept Back 630 - Effect of Sideslip on Aerodynamic
Characteristics at a Mach Nuniber of 1 . 4 With the Wing Twisted and Cambered. NACA RM A3OFO9, 1950.
Lateral-Control Characteristics 8 7 . Scherrer, Richard, and Dennis, David H . : and Dihedral Effect of a Wing-Bod;r Cornbination With a Variable-Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52. NACA RM A50H10, 1951.
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Complete Model Configurations .
8 8 . Campbell, John P., and Toll, Thomas A.: Factors Affecting Lateral Sta- bility and Controllability. NACA RM L8A28a, 1948. * An Investigation of the 8 9 . Fisher, Lewis R., and Michael, William H., Jr.: Effect of Vertical-Fin Location and Area on Low-Speed Lateral Stability Derivatives of a Semitailless Airplane Model. NACA RML5lA10, 1951.
Effect of an Unswept Wing on the 90. Letko, William, and Riley, Donald R.: Contribution of Unswept-Tail Configurations to the Low-Speed Static- and Rolling-Stability Derivatives of a Midwing Airplane Model. NACA TN 2175, 1950- 91. Goodman, Alex: Effects of Wing Position and Horizontal-Tail Position on the Static Stability Characteristics of Models With Unswept and 45O Sweptback Surfaces With Some Reference to Mutual Interference.
NACA TN 2504, 1951.
92. Bird, John D., Lichtenstein, Jacob H., and Jaquet, Byron M.: Investi- gation of the Influence of Fuselage and Tail Surfaces on Low-Speed Static Stability and Rolling Characteristics of a Swept-Wing Model.
NACA 'I" 2741, 1952. (Supersedes TWCA RM L7Rl5.)
93. Letko, Will%m: Effect of Vertical-Tail Area and Length on the Yawing Stability Characteristics of a Model Having a 45O Sweptback Wing.
NACA TN 2358, 1951.
Effect of Fuselage %. Bird, John D., Jaquet, Byron M., and Cowan, John W.: and Tail Surfaces on Low-Speed Yawing Characteristics of a Swept-Wing
-
Model A s Determined in Curved-Flow Test Section of the Langley Stability Tunnel. NACA TN 2483, 1951. (Supersedes NACA RM L & l 3 . ) 95. Goodman, Alex, and Wolhart, Walter D.: Experimental Investigation of the Low-Speed Static and Yawing Stability Characteristics of a 45O Swept- back High-Wing Configuration With Various Twin Vertical Wing Fins.
NACA TN 2534, 1951.
9 6 . Jaquet, Byron M., and Brewer, Jack D.: Effects of Various Outboard and Central Fins on Low-Speed Static-Stability and Rolling Characteristics of a Triangular-Wing Model. NACA RM LgE18, 1949.
9 7 . Goodman, Alex: Effect of Various Outboard and Central Fins on Low- Speed Yawing Stability Derivatives of a 60° Delta-Wing Model. NACA RM L50E12a, 1950.
NACA RM L53108a.
98. B i r d , John D., Fisher, Lewis R . , and Hubbard, Sadie M.: Some Effects of Frequency on the Contribution of a Vertical T a i l t o the Free Aerodynamic Damping of a Model Oscillating i n Yaw. NACA TN 2657, Some Effects of Amplitude and 99. Fisher, Lewis R . , and Wolhart, Walter D.: Frequency on the Aerodynamic Damping of a Model Oscillating Continuously i n Yaw. NACA "'N 2766, 1952.
Influence of Wing and Fuselage on the Vertical-Tail 100. Wolhart, Walter D.: Contribution t o the Low-Speed Rolling Derivatives o f Midwing Airplane Models With 4 5 O Sweptback Surfaces. NACA TN 2587, 1951.
101. Letko, W i l l i a m : A Low-Speed Experimental Study of the Directional C h a r - a c t e r i s t i c s of a Sharp-NosedFuselage Through a Large Angle-of-Attack Range a t Zero Angle of Sideslip. NACA TN 2911, 1953.
102. Jaquet, Byron M., and Fletcher, H. S.: Lateral Oscillatory Characteristics of the Republic F-91 Airplane Calculated by Using Low-Speed Experimental S t a t i c and Rotary Derivatives. NACA RM L53GOl, 1953.
103. Queijo, M. J., and Wells, Evalyn G.: Wind-Tunnel Investigation of the Low-Speed S t a t i c and Rotary S t a b i l i t y Derivatives of a 0.13-Scale Model of the Douglas D-558-11 Airplane i n the Landing Configuration. NACA RM L52GO7, 1952.
104. Johnson, Joseph L.: Damping i n Yaw and S t a t i c Directional S t a b i l i t y of a Canard Airplane Model and of Several Models Having Fuselages of Relatively F l a t Cross Section. NACA RM L5OR3Oa, 1950.
105. Bates, W i l l i a m R.: Low-Speed S t a t i c Lateral S t a b i l i t y Characteristics of a Canard Model Having a 60° Triangular Wing and Horizontal T a i l .
NACA RM L9Jl2, 1949.
106. Delany, Noel K . , and Hayter, Nora-Lee F.: Low-Speed Investigation of a 0.16-Scale Model of the X-3 Airplane - Lateral and Directional C h a r - a c t e r i s t i c s . NACA RM ~ 5 ~ 1 6 , 1951.
Low-Speed Investigation of a Small Triangular Wing 107. Rose, Leonard M.: I11 - S t a t i c S t a b i l i t y With Twin Vertical Fins.
of Aspect Ratio 2.0.
NACA RM A8C03, 1948.
108. McCormack, Gerald M.: Aerodynamic Study of a Wing-Fuselage Combination Ehploying a Wing Swept Back 6 3 O . Aerodynamic Characteristics i n Side- s l i p of a Large-Scale Model Having a 6 3 O Swept-Back Vertical T a i l .
NACA RM AgF14, 1949.
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0 . .e. . e * * . e * e. e
e . e . 0 . . . . e e . . . e .
NACA RM L53108a .
A n Investigation a t Low Speed of a Large-Scale 109. Anderson, Adrien E.: Triangular Wing of Aspect Ratio Two. 111. Characteristics of Wing
With Body and Vertical T a i l . NACA RM AgH04, 1949. -
Tests i n the Ames 40- by 80-Foot Wind Tunnel of an 110. Koenig, David G . : Airplane configuration With a Variable-Incidence Triangular Wing and an All-Movable Horizontal T a i l . NACA RM A53D21, 1953.
Tests i n the Ames 40- by &-Foot W i n d Tunnel of an 111. Koenig, David G.: Airplane Configuration With an Aspect Ratio 3 Triangular Wing and an All-Movable Horizontal T a i l - Longitudinal and Lateral Characteristics.
NACA RM A52L15, 1953.
Tests i n the Ames 40- by 80-Foot 1 1 2 . G r a h a m , David, and Koenig, David G.: Wind Tunnel of an Airplane Configuration With arl Aspect Ratio 2 T r i - angular Wing and an All-Movable Horizontal T a i l - Lateral Characteristics.
NACA R M A5lL03, 1952.
117. Marino, Alfred A . , and Mastrocola, N.: Wind-Tunnel Investigation of the Contribution of a Vertical T a i l t o the Directional S t a b i l i t y of a Fighter-Type Airplane. NACA TN 2488, 1952. (Supersedes NACA RM L7KO3.)
Wind Tunnel Tests on the Yawing Moment 114. Falkner, V . M., and Nixon, H. L.: of a Meteor Model. Rep. No. 11,943, B r i t i s h A.R.C., Nov. 25, 1948.
115. Ross, J. G . , and Lock, R . C.: Wind-Tunnel Measurements of Yawing Moment Due t o Yawing (nr) on a l/5.5 Scaie Model of the Meteor Mark F.111.
I
R . & M. No. 2791, B r i t i s h A . R . C . , 1947.
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116. Spearman, M. Leroy, and Becht, Robert E.: The Effect of Negative Dihedral, I Tip Droop, and Wing Tip Shape on the Low-Speed Aerodynamic Character- i s t i c s of a Complete Model Having a 4 5 O Sweptback W i n g . NACA RM L8JO7, 1948.
117. Goodson, Kenneth W., and Few, Albert G . , Jr.: Low-Speed S t a t i c Longi- tudinal and Lateral S t a b i l i t y Characteristics of a Model With Leading- Edge Chord-Extensions Incorporated on a 40' Sweptback Circular-Arc I Wing o f Aspect Ratio 4 and Taper Ratio 0.50.
NACA RM ~52118, 1952.
118. Schuldenfrei, Marvin, Comisarow, Paul, and Goodson, Kenneth W.: Sta- b i l i t y and Control Characteristics of a Complete Airplane Model Having a Wing With Quarter-Chord Line Swept Back 40°, Aspect Ratio 2.50, and Taper Ratio 0.42.
NACA TN 2482, 1951. (Supersedes NACA RM L7B25. ) , Lateral S t a b i l i t y and Control llg. Goodson, Kenneth W., and Comisarow, Paul: Characteristics of an Airplane Model Having a 42.8' Sweptback Circular- Arc Wing With Aspect Ratio 4.00, Taper Ratio 0.50, and Sweptback T a i l I Surfaces. NACA RM L7G31, 1947.
NACA RM L53108a 3 P 120. Polhamus, Edward C.: Wind-Tunnel Investigation of the Low-Speed S t a b i l i t y and Control Characteristics of a Model With a Sweptback V e e T a i l and a Sweptback Wing. NACA RM L7Kl3, 1948.
i21. K e q , V i l i i a m B., Jr., and Becht, Robert E.: S t a b i l i t y and Control Characteristics a t Low Speed of a l/h-Scale Bell X-5 Airplane Model.
Lateral and Directional S t a b i l i t y and Control. NACA RM L50C17a, 1950.
122. Polhamus, Edward C . , and Becht, Robert E.: Low-Speed S t a b i l i t y Charac- t e r i s t i c s of a Complete Model With a W i n g of W Plan Form. M C A RM L52A25, 1952.
123. Kuhn, Richard E., and Wiggins, James W.: S t a t i c Lateral S t a b i l i t y C h a r - a c t e r i s t i c s of a l/l0-Scale Model of the X-1 Airplane a t High Subsonic Mach Numbers. NACA RM L5lFOla, 1951.
124. Donlan, Charles J., and K u h n , Richard E.: Estimated Transonic Flying Q u a l i t i e s of a Tailless Airplane Based on a Model Investigation.
NACA RM ~ 9 ~ 0 8 , 1949.
and Fournier, Paul G. : Wind-Tunnel 125. Wiggins, James W . , Kuhn, Richard E., Investigation To Determine the Horizontal- and Vertical-Tail Contri- butions t o the S t a t i c Lateral S t a b i l i t y Characteristics of a Complete- Model Configuration a t High Subsonic Speeds. NACA RM L53E19, 1953.
126. K u h n , Richard E., and Wiggins, James W. : Wind-Tunnel Investigation To Determine the Aerodynamic Characteristics i n Steady Roll of a Model at High Subsonic Speeds. NACA RM L52K24, 1953.
127. Purser, Paul E., and Mitchell, Jesse L.: Miscellaneous Directional- S t a b i l i t y Data f o r Several Airplane-Like Configurations F r o m Rocket- Model Tests a t Transonic Speeds. NACA RM ~ 5 2 ~ 0 6 b , 1952.
Effect of Camber and Twist on t h e S t a b i l i t y Character- ~ 8 . White, Maurice D.: i s t i c s of Models Having a 4 5 O Swept Wing As Determined by t h e Free-Fall Method a t Transonic Speeds. NACA RM ~ 5 2 ~ 1 6 , 1952.
and Mitchell, Jesse L . : F l i g h t T e s t s a t Transonic 129. G i l l i s , Clarence L., and Supersonic Speeds of an Airplane-Like Configuration With Thin Straight Sharp-Edge !?ings and T a i l Surfaces. NACA RM L8K04a, 1949.
130. D’Aiutolo, Charles T., and Mason, Homer P.: Preliminary R e s u l t s of t h e Flight In-Jestigation Between Mach Numbers of 0.80 and 1.36 of a Rocket- Powered Model of a Supersonic Airplane Configuration Having a Tapered NACA RM L5OH29ay Wing With Circular-Arc Sections and 40° Sweepback.
1950 -
NACA RM L53108a .
131. D'Aiutolo, Charles T., and Parker, Robert N. : Preliminary Investigation of the Low-Amplitude Damping in Pitch of Tailless Delta- and Swept- NACA RM L52G09,
Wing Configurations at Mach Numbers From 0.7 to 1.35. -
The Aerodynamic Characteristics 132. Spearman, M. Leroy, and Robinson, Ross B.: of a Supersonic Aircraft Configuration With a 4 0 ' Sweptback Wing Through a Mach Number Range From 0 to 2.4 As Obtained From Various Sources.
"ACA FWL52A21, 1952.
An Investigation of a Supersonic Aircraft Configu- 133. Spearman, M. Leroy: ration Having a Tapered Wing With Circular-Arc Sections and 4 0 ° Sweep- Static Lateral Stability Characteristics at Mach Numbers of 1.40 back.
and 1.59. NACA RM L50C17, 1950.
134. Sherrer, Richard, and Dennis, David H.: Damping in Roll of a Missile Configuration With a Modified Triangular Wing and a Cruciform Tail at a Mach Number of 1.52. NACA RMA5U03, 1951.
Wind-Tunnel Investigation of 135. Phelps, E. Ray, and Lazzeroni, Frank A.: the Aerodynamic Characteristics of l/l?-Scale Model of the Northrop MX-775A Missile. NACA RM ~ 5 ~ 2 8 , 1951.
Wind-Tunnel Tests of a 136. Blalock, James E., and Broberg, Ralph F.: 1/3-Scale Model of the Turbojet Version XSUM-N-2 (Grebe) Pilotless Aircraft. Part I - Lateral Stability and Control Characteristics.
Rep. c-156 Aero 759, David Taylor Model Basin, Navy Dept., Oct. 1948.
137. Spahr, J. Richard, and Robinson, Robert A. : Wind-Tunnel Investigation at Mach Numbers of 1.5 and 2.0 of a Canard Missile Configuration.
NACA RM ~5x08, 1951.
138. Darling, J. A., and DeMeritte, F. J.: Static Stability Measurements on l/l7th Scale Modified Shrike at Mach Number 1.87. NAVORD Rep. 2364 (Aeroballistic Res. Rep. 87), U. S. Naval Ord. Lab. (White Oak, Md.), June 10, 1952.
139. Turner, Robert L., and Lobrecht, Dorr, Jr.: Stability and Control Tests of a 0.135-Scale Sperry XAAM-N-2 Model at Mach Number 2.00.
OAL Rep. lU-l?, Ord. Aerophysics Lab. (Daingerfield, Tex.), May 12, 1951.
1 4 0 . Darling, J. A., and DeMeritte, F. J.: Static Stability Measurements on Rascal Missile (MX-776) at Mach Number 1.56.
NAVORD Rep. 2362 (Aero- ballistic Res. Rep. 85), U. S. Naval Ord. Lab. (White Oak, Ma.), June 11, 1952.
NACA RM L53108a I .
Wind-Tunnel Investigation of the RS-9 Meteor at Mach 1 4 1 . Clancy, Thomas M.: Numbers 1.56, 1.87, 2.16, 2.48, and 2.87. NAVORD Rep. 2414 (Aero- ballistic Res. Rep. 9 4 ) , U. S . Naval Ord. Lab. (White Oak, M d . ) , .I July 17, 1952.
Anderson, Arnold W., and Putnam, Russell H.: Wind-Tunnel Tests of a 1 4 2 .
0.65-Scale Model XKD5G-1 Pilotless Target Aircraft. Part I11 - Lateral
and Directional Stability and Control Characteristics. Rep. C-413 Aero 799, The David W. Taylor Model Basin, Navy Dept., Mar. 1951.
1 4 3 . Turner, Robert L., Jr., and Jackson, C. E . : Stability and Control Tests of a 0.135-Scale Sperry XAAM-N-2 Model at Mach Number 1.50. OAL Rep. 112-16, Ord. Aerophysics Lab. (Daingerfield, Tex.), June 22, 1951.
1 4 4 . Turner, Robert L., Jr., and Jackson, C. E.: Stability and Control Tests of a 0.135-Scale Sperry XAAM-N-2 Modei at Mach Number 2 - 5 0 .
OAL Rep. 112-17 (Contract NOrd-9028, Bur. Ord . ) , Ord. Aerophysics Lab.
(Daingerf ield, Tex. ) , June 25, 1951.
145. Spearman, M. Leroy, and Robinson, Ross B.: Wind-Tunnel Investigation of a Ram-Jet Canard Missile Model Having a Wing and Canard Surfaces of Delta Plan Form With TO0 Swept Leading Edges. Longitudinal and Lateral Stability and Control Characteristics at a Mach Nuniber of 1-60.
NACA RM L52E15, 1952.
Wind- 1 4 6 . Hamilton, Clyde V., Driver, Cornelius, and Sevier, John R., Jr.: Tunnel Investigation of a Ram-Jet Missile Model Having a Wing and Canard Surfaces of Delta Plan Form With TO0 Swept Leading Edges.
Force and Moment Characteristics of Various Combinations of Com- ponents at a Mach Number of 1.6. NACA RM L53A14, 1953.
Preliminary Force and Moment Measurements on a Cruciform 1 4 7 . Watts, P. E.: 1.57. Tech. Memo.
Rectangular Wing-Body Combination at Mach Nurdber No. Aero 285, British R.A.E., June 1952.
Supersonic Wind Tunnel Tests of a Made1 of the 1 4 8 . Krieger, Robert H . : North American Guided Missile MX 770 at Mach No. 172. Memo. Rep.
No. 566, Ballistic Res. Labs., Aberdeen Proving Ground, Sept. 1951.
1 4 9 . Beal, R. R.: Roll-Damping and Additional Roll-Control Characteristics of As Determined by Wind-Tunnel Tests of a the Sparrow 14-B at M = 2.50 Rep. No. SM-14062 (Contract NOa( s ) -51-513, 13.5-Percent-Scale Model.
Bur. Aero.), Douglas Aircraft Co., Inc., Dec. 18, 1951.
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20 NACA RM L53108a THREE HIGH-SPEED MODELS a, DEG a , DEG
."VI 4
.50 0 8 1 6 24 a, DEG Figure 1 EFFECTIVE-DIHEDRAL DERIVATIVE C l p FOR THREE HIGH-SPEED MODELS .16r .16r C $ 3 -.I6
[ MODEL II
-.32 - . 3 2 1 1 1 1 , , I l l 0 8 1 6 24 0 8 1 6 24 a, DEG a, DEG C -.I6 MODEL m - $ " A T Figure 2 ....... ...............
NACA FtM L53108a.
DIRECTIONAL-STABILITY DERIVATIVE Cnp FOR THREE HIGH-SPEED MODELS M MODEL I I I I l l J I l l l l l 0 IO 20 0 1 0 20 a. DEG TAIL ON -. 2 VARIATION OF DIRECTIONAL-STABILITY DERIVATIVE CnB WITH HORIZONTAL- TAI L HEIGHT OFF
c "B .2 -4p+ .- bob - ..94
I t I I I I \ , I I I I I I , I I I I I I , 0 8 1 6 24 0 8 1 6 24 0 8 1 6 24 a, DEG a, DEG a, DEG .
Figure 4 0 . 0 . . 0 ... . 0 . 0 . . . 0 0.. 0 .
0 . 0 . 0 . . 0 . . 0 . - - - .
22 NACA RM L53IO8a VARIATION OF EFFECTIVE- DIHEDRAL DERIVATIVE C IP WITH HORIZONTAL-TAIL HEIGHT OFF LOW HIGH I I , 1 1 1 1 1 1 1 1 ~ ~ 1 1 1 1 1 1 1 1 1 1 0 8 1 6 24 0 8 1 6 24 0 8 1 6 a, DEG a, DEG a, DEG EFFECT OF CHORD- EXTENSIONS ON CHARACTERISTICS OF 50 MODEL III M = 0.92 M=O.!
CI - Cm CL
EXTENSION 7
__--- ON
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- OFF .o .o -.04 -.4 CHORD -
-.08 -.8 h EXT.7
U I I I I I I I I I I I C OR 0 c'B -.I6 l I I 1 I I 0 8 1 6 0 8 1 6 24 C2,DEG a,DEG .
Figure 6 VARIATION OF THE DAMPING IN ROLL Clp WITH MACH NUMBER AND ANGLE OF ATTACK .8 .4 r
ClP -.2 om /;/,L50
A
A - 45' A = 4
-.4 --
NACA 65A006 1 1 1 1 1 , , , , , , , 0 4 8 1 2 1 6 20 a, DEG Figure 7 VARIATION OF THE DAMPING IN ROLL Czp WITH ANGLE OF ATTACK M = 0.85
--- 4 60
-.6 i ' " " " I 0 4 8 1 2 1 6 a. DEG Figure 8 NACA RM L53108a TYPICAL VARIATIONS OF THE ROLLING-MOMENT COEFFICIENT C 2 WITH RATE OF ROLL 2~ Pb M = 0.85 8.3.6" 32.6O ' a -.02 EFFECT OF FENCE ON CHARACTERISTICS OF A 45O SWEPT WING M = 0.85 M-0.91 I I I I I , 0 8 1 6 a , DEG Figure 10 I . 0.0 0 0 0 0 0 0 0 0 0.0 0 0.0 0 0 NACA RM L53108a DERIVATIVE FOR THREE HIGH-SPEED MODELS Ci B EXPERIMENT WING-BODY SING-BODY \ VERTICAL TAIL -.08 ~ -.I 6
- L - I
OL I .5 2.5 0 1 5 2.5 0 ' ' 1 5 25 M M M Figure ll DERIVATIVE FOR THREE HIGH-SPEED MODELS Cn B BODY 1 . 5 2 . 0 25 0 1 . 5 2 . 0 25 0 I 5 2x) 2 . 5 3 . 0 H M Figure 12 ..
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