NASA-TN D-6800-1972 Longitudinal aerodynamic characteristics of light twin-engine propeller-driven airplanes《螺旋桨驱动的双发动机轻型飞机的纵向空气动力特性》.pdf

《NASA-TN D-6800-1972 Longitudinal aerodynamic characteristics of light twin-engine propeller-driven airplanes《螺旋桨驱动的双发动机轻型飞机的纵向空气动力特性》.pdf》由会员分享，可在线阅读，更多相关《NASA-TN D-6800-1972 Longitudinal aerodynamic characteristics of light twin-engine propeller-driven airplanes《螺旋桨驱动的双发动机轻型飞机的纵向空气动力特性》.pdf（374页珍藏版）》请在麦多课文档分享上搜索。

1、NASA TECHNICAL NOTEOcOIZI=ZNASA TN D-6800CASE FiLECOPYLONGITUDINAL AERODYNAMICCHARACTERISTICS OF LIGHT, TWIN-ENGINE,PROPELLER-DRIVEN AIRPLANESby Chester H. Wolowicz and RoxanahFlight Research CenterEdwards, Calif. 93523B. YanceyNATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JUNE 197

2、2Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-r_L_Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1. Report No. 2. Government Accession No. 3. Recipients Catalog No.TN D-68004. Title and SubtitleLO

3、NGITUDINAL AERODYNAMIC CHARACTERISTICS OF LIGHT, TWIN-ENGINE, PROPELLER-DRIVEN AIRPLANES7. Author(s)Chester H. Wolowicz and Roxanah B. Yancey9. Performing Organization Name and AddressNASA Flight Research CenterP. O. Box 273Edwards, California 9352312. Sponsoring Agency Name and AddressNational Aero

4、nautics and Space AdministrationWashington, D. C. 205465. Report DateJune 19726. Performing Organization Code8. Performing Organization Report No.H-64610. Work Unit No.736-05-00-01-2411. Contract or Grant No.13. Type of Report and Period CoveredTechnical Note14. Sponsoring Agency Code15. Supplementa

5、ry Notes16. AbstractThis report documents representative state-of-the-art analyticalprocedures and design data for predicting the longitudinal static anddynamic stability and control characteristics of light, propeller-drivenairplanes. Procedures for predicting drag characteristics are alsoincluded.

6、The procedures are applied to a twin-engine, propeller-drivenairplane in the clean configuration from zero lift to stall conditions.The calculated characteristics are compared with wind-tunnel andflight data. Included in the comparisons are level-flight trim character-Istics, period and damping of t

7、he short-period oscillatory mode, andwindup-turn characteristics. All calculations are documented.“17. Key Words (Suggested by Author(s)Light airplaneAerodynamic characteristics - prediction18. Distribution StatementUnclassified - Unlimited19. Security Classf. (of this report)Unclassified20. Securit

8、y Classif. (of this page) 21. No. of PagesUnclassified 36122. Price“$6.00For sale by the National Technical Information Service, Springfield, Virginia 22151Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1ii, Provided by IHS Not for ResaleNo reproduc

9、tion or networking permitted without license from IHS -,-,-CONTENTSTABLES RELATED TO SUBJECT AIRPLANE .FIGURES COMPARING CALCULATED CHARACTERISTICS .SUMMARY i. 0 INTRODUCTION 2.0 SCOPE OF THE STUDY .3.0 THE AIRPLANE 3.1 Center-of-Gravity Positions Used in the Analysis .3.2 Geometric Parameters of th

10、e Wing and Horizontal TailUsed in the Analysis 3.2.1 Symbols .4.0 PREDICTION OF PROPELLER-OFF AERODYNAMICCHARACTERISTICS 4. i Wing and Horizontal-Tail Airfoil Section Characteristics 4.1. i Symbols . 4.2 Lift Characteristics of the Wing and Horizontal Tail .4 2 1 Symbols4.3 Lift Due to Fuselage and

11、Nacelles .4.3.1 Symbols 4.4 Lift Due to Combined Wing-Fuselage-Nacelle .4.4.1 Symbols 4.5 Cmo and Aerodynamic Center of the Wing and HorizontalTail .4.5.1 Symbols .4.6 Wing-Fuselage Pitching Moment at Zero Lift 4.6.1 Symbols .4.7 Fuselage and Nacelle Pitching Moments .4.7. I Symbols .4.8 Wing-Fusela

12、ge-Nacelle Pitching Moments .4.8.1 Contributing Factors to V_;ing-Fuselage-NacellePitching Moments .4.8.2 Static Margin of Wing-Fuselage-Nacelles .4.8.3 Pitching-Moment Coefficient of Wing-Fuselage-Nacelles .4.8.4 Symbols .4.9 Downwash and Dynamic Pressure at the Horizontal Tail 4 9 1 Downwash4.9.2

13、Dynamic-Pressure Ratio .4.9.3 Symbols 4. i0 Lift of the Complete Airplane (5 e = 0 ) 4. I 0.1 Symbol s 4. II Pitching Moments of the Complete Airplane (5 e = 0 ) .4.1 i. i Symbols 4.12 Drag of the Complete Airplane .4.12.1 Zero-Lift Drag of Wing, Horizontal Tail, andVertical Tail .4.12.2 Zero-Lift D

14、rag of Fuselage and Nacelles .4.12.3 Zero-Lift Interference Drag of Wing-Fuselage,Tail-Fuselage, and Wing-Nacelles Pageviix12236131315272937384648555660606464686871727587879092109111lt7118122122123124.oo111Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

15、,-,-5.06.0CONTENTS- Continued4.12.4 Drag of Wing and Horizontal Tail at Angle ofAttack .4.12.5 Drag of Fuselage and Nacelles at Angle ofAttack .4.12.6 Wing-Fuselage Interference Drag at Angle ofAttack .4.12.7 Cooling Drag 4.12.8 Summary Drag of the Complete Airplane 4.12.9 Symbols .4.13 Effect of Ho

16、rizontal Taft and Tab Deflection on Lift andPitching Moments .4.13.1 Lift of the Horizontal Tail in the Linear Range 4.13.2 Maximum Lift of the Horizontal Tail 4.13.3 Lift Curves of the Horizontal Tail Through Stall . . .4.13.4 Lift and Pitching-Moment Curves of the AirplaneIncluding the Effect of E

17、levator Positions 4.13.5 Symbols .4.14 Horizontal-Tail Hinge Moments and Stick Forces 4.14.1 Horizontal-Tail Hinge Moments 4.14.2 Stick Forces 4.14.3 Symbols .PREDICTION OF POWER-ON AE RODYNAMIC CHAR-ACTERISTICS .5.1 Power Effects on Lift 5.1.1 Tail-Off Lift Characteristics With Power On .5.1.2 Hori

18、zontal-Tail Contribution to Lift 5.1.3 Net Characteristics of the Subject Airplane 5.1.4 Symbols .5.2 Power Effects on Pitching Moments .5.2.1 Symbol s .5.3 Power Effects on Drag 5.3.1 Symbols .5.4 Power Effects on Horizontal-Tail Hinge Moments andStick Forces 5.4.1 Symbols .DYNAMIC CHARACTERISTICS

19、6.1 Lift Due to Dynamic Motions 6.1.1 Lift Due to pitch Rate, CLq 6.1.2 Lift Due to Vertical Acceleration, CL_ .6.1.3 Symbols .6.2 Pitching Moments Due to Dynamic Motions .6.2.1 Pitching Moments Due to Pitch Rate, Cmq 6.2.2 Pitching Moment Due to Vertical Acceleration,Cm_ .6.2.3 Pitching Moments Due

20、 to Pitch Rate and VerticalAcceleration in Short-Period TransientOscillations, (Cmq + Cm_) .ivPage12712913013113113215615616016116216518418419119221521621722122322425626228228530030131031131131331532532532833O1Provided by IHS Not for ResaleNo reproduction or networking permitted without license from

21、 IHS-,-,-CONTENTS - Concluded6.2.4 Symbols .6.3 Short-Period Transient Oscillation Characteristics .6.3.1 Symbols .6.4 Windup-Turn Characteristics .6.4.1 Variation of Otrim and 5etri m With LoadFactor 6.4,2 Variation of Hinge Moments and Stick ForcesWith Load Factor 6.4.3 Symbols .REFERENCES .Page33

22、1340341346346349351359Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLES RELATED TO SUBJECTAIRPLANEPage3-1 MANUFACTURER S PHYSICAL CHARACTERISTICS OFTHE SUBJECT AIRPLANE 43.2-1 PERTINENT WING AND HORIZONTAL-TAIL GEOMETRICPARAMETERS USED IN THE AN

23、ALYSIS 9PREDICTION OF PROPELLER-OFF AERODYNAMIC CHARACTERISTICS4. i-I AIRPLANE WING AND HORIZONTAL-TAIL AIRFOILSECTION CHARACTERISTICS 164.2-i LIFT CHARACTERISTICS OF AIRPLANE WING ANDHORIZONTAL TAIL . 314.3-1 CONTRIBUTION OF FUSELAGE AND NACELLES TOAIRPLANE LIFT COEFFICIENT 404.4-1 WING LIFT OF AIR

24、PLANE INCLUDING MUTUAL WING-FUSELAGE INTERFERENCE 504.4-2 SUMMARY OF WING-FUSELAGE-NACELLE LIFT 514.5-1 Cmo AND AERODYNAMIC CENTER OF WING AND57HORIZONTAL TAIL .4.6-1 WING-FUSELAGE PITCHING MOMENTS OF AIRPLANE ATZERO LIFT 624.7-1 FUSELAGE AND NACELLE PITCHING MOMENTS OFAmPLANE. G64.7-2 TABULAR INTEG

25、RATION OF FUSELAGE PiTCtIN6-MOMENT PARAMETERS 674.8.1-1 WING PITCHING MOMENTS OF THE AIRPLANE . 804.8.1-2 “ FREE MOMENTS“ OF FUSELAGE AND NACELLES 814.8.3-1 PITCHING MOMENTS OF WING-FUSELAGE-NACELLESCONFIGURATION . 834.9. i-i PERTINENT PARAMETERS FOR COMPUTING AVERAGEDOWNWASH AT HORIZONTAL TAIL OF S

26、UBJECTAIRPLANE 964.9.1-2 SUMMARY CALCULATION OF AVERAGE DOWNWASH ATHORIZONTAL TAIL OF SUBJECT AIRPLANE . 974.9.2-2 DYNAMIC-PRESSURE RATIO AT THE HORIZONTAL TAILOF THE SUBJECT AIRPLANE 994.10-1 LIFT OF HORIZONTAL TAIL IN THE PRESENCE OF THEFUSELAGE (6e = 0) 1134.10-2 LIFT OF THE COMPLETE AIRPLANE (6e

27、 = 0) . 1144.11-1 PITCHING MOMENTS OF THE COMPLETE AIRPLANE(5e 0) 1194.12. i-I SURFACE ROUGHNESS HEIGHT k 1374.12.1-2 ZERO-LIFT DRAG OF WING, HORIZONTAL ANDVERTICAL TAILS 1374.12.2-1 ZERO-LIFT DRAG OF FUSELAGE AND NACELLES . 1384.12.3-1 ZERO-LIFT DRAG OF THE COMPONENTS 1394.12.4-1 DRAG OF WING AND H

28、ORIZONTAL TAIL DUE TO LIFT . 140viProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLES - ContinuedPage4.12.5-1 DRAG DUE TO LIFT OF FUSELAGE AND NACELLES 1424.12.8-1 DRAG OF THE COMPLETE AIRPLANE (6e = 0). 1434.13.1-1 LIFT CONTRIBUTION OF THE HORIZO

29、NTAL TAIL WITHTAB-TO-ELEVATOR GEAR RATIO OF i.5 1704.13.2-1 MAXIMUM LIFT COEFFICIENTS OF THE HORIZONTALTAIL 1734.13.4-1 EFFECT OF ELEVATOR DEFLECTION ON LIFT ANDPITCHING MOMENTS OF THE AIRPLANE . 1744.14.1-1 LIFT CHARACTERISTICS OF HORIZONTAL TAIL ALONE INTHE PRESENCE OF THE BODY AS A FUNCTION OF a_

30、hAND 6e, WITH TAB GEARED IN RATIO OF6tab/6e = 1.5 1974.14.1-2 PERTINENT RELATIONS FOR HORIZONTAL-TAIL HINGEMOMENTS 1984.14.1-3 HORIZONTAL-TAIL TAB CHARACTERISTICS 2004.14.1-4 HORIZONTAL-TAIL HINGE-MOMENT CHARACTERISTICS . . . 202PREDICTION OF POWE R-ON CHARAC TE RISTICS5.1.1-1 LIFT DUE TO DIRECT ACT

31、ION OF THE PROPELLERFORCES . 2305.1.1-2 WING-LIFT INCREMENTS DUE TO PROPELLER SLIP-STREAM EFFECTS . 2325.1.1-3 TAIL-OFF LIFT CHARACTERISTICS WITH POWER ON . 2355.1.1-4 POWER EFFECTS ON MAXIMUM LIFT 2365.1.2-1 EFFECT OF ELEVATOR DEFLECTION ON LIFT WITHPOWER ON 2375.2-1 PITCHING-MOMENT INCREMENTS DUE

32、TO PROPELLERFORCES . 2675.2-2 ZER O-LIFT PITCHING-MOMENT INCREMENT DUE TOPOWER 2685.2-3 PITCHING-MOMENT INCREMENT DUE TO POWER-INDUCED CHANGE IN WING LIFT . 2705.2-4 PITCHING-MOMENT INCREMENT DUE TO POWER EFFECTON NACELLE FREE MOMENTS 2715.2-5 TAIL-OFF PITCHING-MOMENT CHARAC TE RISTICS WITHPOWER ON

33、2725.2-6 EFFECT OF ELEVATOR DEFLECTION ON PITCHINGMOMENTS WITH POWER ON 2735.3-1 ZERO-LIFT DRAG INCREMENTS DUE TO POWER . 2895.3-2 INDUCED-DRAG INCREMENT DUE TO POWER . 2905.3-3 CHANGE IN COOLING-SYSTEM DRAG DUE TO POWER . 2945.3-4 POWER-ON DRAG OF THE COMPLETE AIRPLANE . 2955.4-1 HORIZONTAL-TAIL TA

34、B CHARACTERISTICS 3045.4-2 HORIZONTAL-TAIL HINGE-MOMENT CHARACTERISTICS . . 305DYNAMIC CHARACTERISTICS6.1.1-1 LIFT DUE TO PITCH RATE, CLq 319viiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6.1.2-16.2.1-16.2.2-16.4.1-16.4.2-1TABLES - ConcludedLIFT

35、DUE TO VERTICAL ACCELERATION, CL Sw = 178 sq ft . 1154.11-1 Comparison of predicted airplane pitching moments with wind-tunnel data. 6 e = 0; Sw = 178 sq ft; center of gravity =0.10 w 1204.12.8-1 Comparison of predicted airlSlane drag characteristics withwind-tunnel data. 5 e = 0; propellers off; Sw

36、 = 178 sq ft. 1524.13.4-1 Comparison of predicted propeller-off lift and pitching-moment characteristics of the airplane with wind-tunnel dataas a function of o_b and 6 e. Sw= 178 sq ft; 5tab/6 e = 1.5(propeller-off wind-tunnel data obtained from propeller-ondata at T% = 0 with propeller effects cal

37、culated out); centerof gravity = 0. 106 w . 1824.14.1-10 Comparison of calculated and wind-tunnel-determined hinge-moment coefficients of the horizontal tail. 5tab/Se = 1.5;wind-tunnel data at T_ = 0 assumed equivalent to propeller-off condition . 214POWER-ON CHARACTERISTICS5.1.2-4 Comparison of cal

38、culated and experimentally determined (ref. 2)downwash at the horizontal tail of the subject airplane atseveral power settings . 2535.1.3-1 Comparison of calculated and wind-tunnel-determined variationof C L with oeb at different power conditions and elevatordeflections . 2555.2-2 Comparison of calc

39、ulated and wind-tunnel-determined tail-offlift and pitching-moment characteristics at T_ = 0.44 andcenter of gravity = 0.10_ w . 2755.2-3 Comparison of calculated and wind-tunnel-determined variationof Cm with c_b at different power conditions and elevatordeflections. Center of gravity - 0. 106 w .

40、2765.2-4 Comparison of calculated and wind-tunnel-determined variationof C m with C L at different power conditions and elevatordeflections. Center of gravity - 0.10_ w 277ixProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5.2-55.2-65.2-75.2-85.3-45.3

41、-55.4-15.4 -26.2.3-16.3-16.3-26.4.2-1FIGURES - ConcludedPageComparison of neutral-point characteristics determined frommodified calculated and wind-tunnel pitching-momentcharacteristics. Center of gravity = 0.10_ w 278Comparison of the variation of calculated and _qnd-tunnel-determined pitch-control

42、 effectiveness with thrust coefficientand angle of attack 279Comparison of calculated static pitch, Cmc d and control ef-fectiveness, Cm_ e, with wind-tunnel and flight-determinedvalues as a function of angle of attack. Center of gravity =O. 12_ w . 280Comparison of calculated C L, ab and 5 e charac

43、teristics fortrim level flight conditions with those obtained from wind-tunnel and flight data as a function of calibrated airspeed.Center of gravity = 0.12_ w . 281Comparison of calculated and wind-tunnel-determined variationof C D with _b at different power conditions. 5e = 0 298Comparison of calc

44、ulated and wind-tunnel-determined variationof C D with C L at different power conditions. 5 e = 0 299Comparison of calculated and _qnd-tunnel-determined variation ofhinge moment Chh(t ) with angle of attack at different powerconditions and elevator deflections . 308Comparison of calculated hinge-mom

45、ent and stick-force character-istics in level flight with those obtained from wind-ttmnel andflight data as a function of airspeed. Altitude = 6000 ft;center of gravity -=-0.12_ w 309Comparison of calculated Cmq + Cmcenter of gravity = 0.12Cw; V = 220 ft/sec. 358Provided by IHSNot for ResaleNo repro

46、duction or networking permitted without license from IHS-,-,-LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF LIGHT, TWIN-ENGINE,PROPE LLER-DRIVEN AIRPLANE SChester H. Wolowicz and Roxanah B. YanceyFlight Research CenterSUM MA RYRepresentative state-of-the-art analytical procedures and design data for pr

47、e-dicting the subsonic longitudinal static and dynamic stability and control characteristicsof light, propeller-driven airplanes are documented. Procedures for predicting dragcharacteristics are also included.The procedures are applied to a twin-engine, propeller-driven airplane in the cleanconfigur

48、ation to determine the lift, pitching-moment, and drag characteristics fromzero lift to stall conditions. Also determined are level-flight trim characteristics,period and damping of the short-period oscillatory mode, and windup-turn character-istics. All calculations are documented.The calculated lift characteristics correlated well with full-scale wind-tunnel dataas a function of angle of attack, elevator settings, and power conditions.The calculated drag characteristics also correlated well with full-scale wind-tunnel data as a function of angle o