REG NACA-TR-868-1947 Summary of lateral-control research.pdf

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1、NATIONAL ADVISORY COMMITTEE - FOR AERONAUTICS REPORT No. 868 SUMMARY OF LATERAL-CONTROL RESEARCH By LANGLEY RESEARCH STAFF COMPILED by THOMAS A. TOLL 1947 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AERONAUTIC SYMBOL 1: FUNDAMENTAL AND DERIVED UN

2、ITS I Metric I English I .I . .unit - unit +ngth- 1 - Ez - - : meter- _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ I second _ weight of 1 kilogram _ 1 horsepower (metric) _ _ _ _ _ _ _ _ _ _ _ _ _ _ l I horsepower- _ _ _ _ _ _ _ _ _ _ kilometers per hour- W meters per second _ mps miles per hour- _ _ _ feet per

3、second _ 2. GENERAL SYMBOLS W v m I. P Weight=mg ._ V Standard acceleration of gravity=93Q665 m/s Kinematic visdosity p or 32.1740 ft/sec= Density (mass per unit volume) MassJ L Standard density of dry air, 0.12497 kg-m%* at 15O C and 760 mm; or 0.002378 lb-ftL4 sets Momen! of inertia=m. (Indioate t

4、is of unspecific weight of “standard” air, 1.2255 kg/m* or 0.07651 lb/cu ft radius of gyration k by proper subscript.) 2 . Co or for an airfoil of 1.0 m chord, 100 mps, the corresponding Reynolds number is 6,865,OOO) Angle of attack Angle of downwash Angle of attack, infinite aspect ratio Angle of a

5、ttack, induced Angle of attack, absolute (measured from zero- -lift position) Flight-path angle . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. c- - - TECH LIBRARY KAFB, NM REPORT No. 868 SUMMARY OF LATERAL-CONTROL RESEARCH By LANGLEY RESEARCH ST

6、AFF COMPILED by THOMAS A. TOLL Langley Memorial Aeronautical Laboratory Langley Field, Va. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-National Advisory Committee for Aeronautics Headquarters, 1724 F Street NW, Washington 25, D. C. Created by a

7、ct of Congress approved March 3, 1915, for the supervision and direction of the scientific study of the problems of flight (U. S. Code, title 49, sec. 241). Its membership was increased to 15 by act approved March 2, 1929. The members are appointed by the President, and serve as such without compens

8、ation. JEROME C. HUNSAKER,. SC. D., Cambridge, Mass., Chairman ALEXANDER WETMORE, SC. D., Secretary, Smithsonian Institution, Vice Chairman HON. JOHN R. ALISON, Assistant Secretary of Commerce. VANNEVAR BUSH, SC. D., Chairman, Research and Development Board, Department of National Defense. EDWARD U.

9、 CONDON, PH. ,D., Director, National Bureau of Standards. DONALD B. DUNCAN, Vice Admiral, Deputy Chief of Naval Operations (Air). R. M. HAZEN, B. S., Chief Engineer, Allison Division, General Motors Corp. WILLIAM LITTLEWOOD. M. E., Vice President, Engineering, American Airlines System. THEODORE C. L

10、ONNQUEST, Rear Admiral, Assistant Chief for Research and Development, Bureau of Aeronautics, Navy Department. EDWARD M. POWERS, Major General, United States Air Force, Deputy Chief of Staff, Materiel. ARTHUR E. RAYMOND, M. S., Vice President, Engineering, Douglas Aircraft Co. FRANCIS W. REICHELDERFE

11、R, SC. D.; Chief, United States Weather Bureau. CARL SPAATZ, General, Chief of Staff, United States Air Force. ORVILLE WRIGHT, SC. D., Dayton, Ohio. THEODORE P. WRIGHT, SC. D., Administrator of Civil Aero- nautics, Department of Commerce. HUGH L. DRYDEN, PH. D., Director of Aeronautical Research JOH

12、N F. VICTORY, LLM., Executive Secretary JOHN W. CROWLEY, JR., B. S., Associate Director of Aeronautical Research E. H. CHAMBERLIN, Executive Oficer HENRY J. E. REID, SC. D., Director, Langley Memorial Aeronautical Laboratory, Langley Field, Va. SMITH J. DEFRANCE, B. S., Director Ames Aeronautical La

13、boratory, Moffett Field, Calif. EDWARD R. SHARP, LL. B., Director, Flight Propulsion Research Laboratory, Cleveland Airport, Cleveland, Ohio TECHNICAL COMMITTEES AERODYNAMICS OPERATING PROBLEMS POWER PLANTS FOR AIRCRAFT SELF-PROPELLED GUIDED MISSILES AIRCRAFT CONSTRUCTION INDUSTRY CONSULTING Coordin

14、ation of Research Needs of Military and Civil Aviation Preparation of Research Programs Allocation of Problems Prevention of Duplication Consideration of Inventions LANGLEY MEMORIAL AERONAUTICAL LABORATORY, AMES AERONAUTICAL LABORATORY, Langley Field, Va. Moffett Field, Calif. FLIGHT PROPULSION RESE

15、ARCH LABORATORY, Cleveland Airport, Cleveland, Ohio Conduct, under uni$ed control, for all agencies, of scientific research on the fundamental problems of flight OFFICE OF AERONAUTICAL INTELLIGENCE, Washington, D. C. Collection, classi$cation, compilation, and dissemination of scientific and technic

16、al information on aeronautaca II Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 I CONTENTS Page 1 1 I. CRITERIONS USED IN LATERAL-CONTROL SPECIFICATIONS ROLLING PERFORMANCE_-_-_- CONTROLFORCES-_-_- STICK OR WHEEL TRAVEL- ADVERSE YAW-_-_- LAGIN RES

17、PONSE_-_-_-_- CONTROL-FREE STABILITY-_- II. FACTORS INVOLVED IN THE LATERAL-CONTROL PROBLEM LATERAL ANEuvERABILITY-_- Concept of Lateral Maneuverability _ - _ Helix angle _ - _ - _ -_- _ Controlforce_-_-_ Effects of Wing Twist- -_ Effect.s of Control-System Stretch- - _ _ - _ _ _ _- - _ _ _ _ - _ _

18、_ Effects of Adverse Yaw _-_c-_ -_ Weathercock stability- _ _ _ _ - _ _ _ _ _ _ _ _ _-_ _ _ Dihedral_-_- Effects of Aspect Ratio- - - _ _ _ _ _ _-_ _ _ Effects of altitude- _ _ _-_-_-_ Effects of Radii of Gyration and Wing Loading- _ _ _ _ CONTROL-FREE STABILITY-_- FLUTTER-_-_-_- 3 3 3 4 5 7 7 7 7 7

19、 7 8 9 9 III. TESTING PROCEDURES AND APPLICATION OF EXPERIMENTAL RESULTS FLIGHT INESIGATIONS- Procedure for Determining Rolling Performance _ _ _ _ _ _ _ _ Description of maneuver- _ _ _ _ _- _ _ _ _ _ _ _ _ _ _ _ Variables measured _ z _ - _ Presentation of data _-_ -_-_-_- _ Procedure for Determin

20、ing Adverse Yaw- _ _ _ _-_ _ _ _ Description of maneuver _ Variables measured _ _-_ _ _ _ _ _-_-_ _ _ _ Presentation of data _ - _ Procedure for Determining Aileron Trim Changes with Speed-_-_-_-_-_- WIND-TUNNEL INVESTIGATIONS-_-_-.- Two-Dimensional Models- _ _ _ -_ _-_ _-_ _- _ _ _ _ _ _ Finite-Spa

21、n Models- _ _ _ _ _ _ _ _-_ _ _ _ _-_ _ _ _ _ _ IV. CHARACTERISTICS OF LATERAL-CONTROL DEVICES 9 9 9 10 10 10 10 11 11 11 11 11 13 CONVENTIONALFLAP-TYPE AILERONS_-_-_- 14 Plain Ailerons _-_ - _-_ -_- _ 15 Hinge-moment characteristics- _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 15 Lift characteristics- _- _ _ _ _

22、 _-_ _-_ _ _ _ 17 Pitching-moment characteristics- _ - _ _ _ _-_ _ _ _ _ 19 Flighttests_-_- 20 CONVENTIONALFLAPTYPE AILERONS-Continued PagO Ailerons Having Exposed-Overhang Balances _ 20 Hinge-moment characteristics _ _ _-_ _-_ 20 Critical deflection _ _ _ _ _ _ _ _ _ _ _ _- _ _ _ _ _ _ _ _ _ _ 24 E

23、ffectiveness- _ _ _ _ _ _- _ _ 24 Design considerations _ - _-_ 24 Flight tests of Frise ailerons- _ -_-_ _ - _ 27 Ailerons Having Sealed Internal Balances- _ 30 Ailerons Having Linked Tabs _ - _ -_-_-_-_ 33 Comparisons of Various Balancing Devices- _ _-_-_ _ 36 Hinge-moment characteristics _ - _ -

24、36 Effect of angle of rig _-_ 37 Rolling performance_- _ - _ -_ 37 Application to Arrangements Involving Full-Span Flaps- 38 Flap-trailing-edge ailerons _ 38 Drooped ailerons _-_ -_ 38 Ailerons with retractable flaps _ _ _ - - _ _ _ _ - - _ _ _ _ - - _ _ 42 Effects of Air-Flow and Wing-Surface Condi

25、tions- _ _ _ _ _ _ - 42 Boundary-layer effects- _ - 42 Mach number effects- _- _-_ _c_ 45 Surface-covering distortion- _-_ _ _-_ _ _ _-_ _ _ _-_ _ 48 SPOILER DEVICES_-_-_ 50 Hinged-Flap Spoilers- _ _-_ _ _- _ _ _ _ _ -_-_-_- 51 Retractable-Arc Spoilers- _ _ _ _ _ _ - _ _ _ _ _ _ _ - _ _ _ _ _ _ _ _

26、- - _ - _ _ 51 Slot-Lip Ailerons-_ _ - _ -_ 53 Plug-Type Spoiler Ailerons- _ _ _ _ _ _ _ _ _ _ _- - _ 53 Effects of Mach Number- _ -_-_-_- _ -_ 55 V. BOOSTER MECHANISMS AERODYNAMIC BOOSTERS_-_-_-_- 55 Equations for Control Force- -_-_ - _ 55 Characteristics of Spring-Tab Ailerons-_ _ 56 Special Spri

27、ng-Tab Designs _ - _ -_-_-_ 57 Useofpreioad_-_-_-_- 57 . Geared spring tab-_-_- 58 Detached tab_-_-_-_-_-_ 58 Other Aerodynamic Boosters _._ - _ -_-_-_ 58 MECHANICAL BOOSTERS-_- 58 VI. STRUCTURAL ASPECTS INTEGRITY OF AIRPLANE-_- ROLLING PERFORMANCE-_-_- CONTROL FORCES_-_-_- 58 59 59 VII. APPLICATION

28、 OF EQUATIONS AND DESIGN CHARTS ILLUSTRATIVE EXAMPLE-_-_-_- DISCUSSION-_-_- VIII. STATUS OF LATERAL-CONTROL RESEARCH CONVENTIONALFLAP-TYPE AILERONS-_-_-_,_ Rolling Performance- _ -_- _ Hinge Mornents_- SPOILER DEVICES_-_-_- LATERALCONTROLWITHSWEPTWINGS_-_-_-_-_ APPENDIX-DEFINITIONS OF SYMBOLS_- _ RE

29、FERENCES_-_-_- 59 63 63 63 63 65 65 07 69 III Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-REPORT No. 868 SUMMARY OF LATERAL-CONTROL RESEARCH By LANGLEY RESEARCH STAFF COMPILED by THOMAS A. TOLL SUMMARY A summary has been made qf the available inf

30、ormation on lateral control. A discussion is given of the criterions used in lateral-control speci$cations, of the factors involved in obtaining satisfactory lateral control, and of the methods employed in making lateral-control investigations in flight and in wind tunnels. The auailable data on con

31、ventional flap-type ailerons having ,various types of aerodynamic balance are presented in a form convenient for use in design. The characteristics of spoiler devices and booster mechanisms are discussed. The f$ects of Mach number, boundary layer, and distortion of the wing or of the lateral-control

32、 system are considered insofar as the available information permits. An example is included to illustrate the use of the design data. The limitations qf the available information and some of the lateral-control problems that remain to be solud are indicated. INTRODUCTION The lateral-control research

33、 that had been conducted by the NACA prior to 1937, and that was summarized in refer- ence 1, was concerned primarily with the design of latcral- control devices having sufficient cffectivcness to enable the pilot of an airplane to Beep the wings level at all normal flight speeds. In order to meet t

34、hat condition large rolling- moment coefficients are required only at speeds approaching the stall; consequently, the provision of adequate rolling performance is principally a problem of the size of the device, the aerodynamic balance being of only secondary importance even for moderately large air

35、planes. Between 1937 and 1941 a study was made of the lateral- control characteristics of a large number of combat and non- combat airplanes. The results of that study, reported in reference 2, indicated that the provision of lateral control that is sufficient only to keep the wings level is inadequ

36、ate, and that a certain minimum standard of rolling performance is desirable for any type of airplane, even at high speeds. Subsequent experience has indicated that combat airplanes may be required to perform rapid rolling maneuvers near maximum speed. The problem of providing aerodynamic balance fo

37、r light control forces at high speeds therefore has become at least as important as the problem of providing adequate effectiveness of the lateral-control device. In order to meet the requirements for light control forces, the designer has the choice of relying entirely either on aero- dynamic balan

38、ce or on some form of booster mechanism, or of combining a booster mechanism of low capacity with a small amount of aerodynamic balance. In any case, the control forces of fighter airplanes of average size may have to be reduced by amounts corresponding to as much as 95 percent of the unbalanced ail

39、eron hinge moments (refer- ence 3). Some of the considerations relating to the provision of light control forces, as well as to other lateral-control problems, are discussed in reference 4. The purpose of the present paper is to summarize rather completely the available information on lateral contro

40、l, to point out the limitations of the available information, and to indicate some of the problems that remain to be solved. No new investigations were at,tempted in preparing the present paper, although some of the data and analyses have not previously been published. The symbols used in presenting

41、 the results are defined in the appendix. Figures that give data for use in design are listed in table I. I. CRITERIONS USED IN LATERAL-CONTROL SPECIFICATIONS In order to apply the results of theoretical and experi- mental studies to the design of satisfact,ory lateral-control clevices, the requirem

42、ents for satisfactory lateral control must bc specified exactly. Lateral-control specifications have been limited to the unstallecl flight range because the charac- teristics at and above the stall usually are very erratic. The lateral behavior in stalled flight usually is included in considerations

43、 of stalling characteristics. The first comprehensive set of lateral-control specifications, which represent the present NACA recommendations, was published in reference 5. Lateral-control specifications prepared in 1945 by the Air Technical Service Command, Army Air Forces (reference 6), and by the Bureau of Aero- nautics, Navy Department (reference 7), a