1、NASACONTRACTOR REPORT A DESIGN SUMMARY OF STALL CHARACTERISTICS OF STRAIGHT WING AIRCRAFT by M. A. McVeigb md E. Kisielowski Prepared by DYNASCIENCES CORPORATION SCIENTIFIC SYSTEMS DIVISION Blue Bell, Pa. for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JUN
2、E 1971 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TECH LIBRARY KAFB, NM -_- _ . “ . - “ _ I 00607b3 1. Report No. 2. Government Accession No. 3. Recipient. rormluy I.u. NASA CR-1646 - 4. Title andsubtitle - - 5. Report Date A DESIGN SUMMARY OF S
3、TALL CHARAC!iTBISTICS OF STRAIGHT WING AIRCRAFT June lg7 6. Performing Organization Code . . - - - 7. Author(s) DCR-705 M. A. McVeigh and E. Kisielowski 8. Performing Organization Report No. “ “. . 10. Work Unit No. 9. Performing Organization Name and Address 126-13-10-06-23 Dynasciences Corporation
4、 Scientific Systems Division I I 11. Contract or Grant No. Blue Bell, Pennsylvania NASl-8389 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report NATIOW AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. 20546 1- 14. Sponsoring Agency Code “ “ - _ I 15.
5、Supplementary Notes . . .- - . . “_ 16. Abstract ._ . .“ . - . A method of wing design using lifting line theory described in NACA Reports 865 and 1090 has been computerized and used to study the parameters which affect wing stall characteristics. The results of the study and the computer programare
6、described. The effects of airfoil section variations, Reynolds number, aspect ratio, wing twist ad taper ratio are presented in design chart form. - _i .- . - - - 17. Key Words (Suggested by Author(s) ) Strip Theory Subsonic Wing Design Computer Program . -. . 19. Security Classif. (of this report)
7、18. Distribution Statement Unclassified - Unlimited Unclassified I . Unclassified 226 “. “ - For sale by the National Technical Information Service, Springfield, Virginia 22151 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. - Provided by IHSNot fo
8、r ResaleNo reproduction or networking permitted without license from IHS-,-,-SUMMARY Presented in this report is a comprehensive review of the existing tech.nica1 literature and a design summary of stall ch.aracteristics applicable to light straigh.t wing aircraft. These characteristics are obtained
9、 with th.e aid of a digital computer program which. utilizes the most up to date analytical methods employing lifting line theory and the available exper- imental test data for wing section characteristics. The computer results are presented in th.e form of stall ch.arts suitable for preliminary des
10、ign purposes. Based on th.e extensive parametric study covering a total of 331 different aircraft configurations, it can be concluded that in modern airplane design satisfactory stalling characteristics can be readily built in with no apprecia- ble loss in airplane performance or handling qualities.
11、 A proper combination of wing taper, twist and type of airfoil sections with. minor post-design fixes, if required, can in most cases provide satisfactory wing stall characteristics. iii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I - Provided by
12、 IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-FOREWORD This report presents a design summary of stall ch.aracter- istics of straigh.t wing aircraft. Th.e work was performed by th.e Scientific Systems Division (SSD) of the Dynasciences CorDoration, Blue Bell,
13、Pennsylvania, for the National Aeronautics and Snace Administration (NASA), Langley Research Center, Hampton, Virginia, under contract number NAS 1-8389 during the period from July 1968 through SeDtember 1969. Th.e NASA technical representatives were Mr. Robert T. Taylor and Mr. William J. Alford, J
14、r. The contributions of the NASA technical personnel to this work are gratefully acknowledged. Acknowledgement is also extended to NASA computer personnel, especially Mrs. Belinda Adams, for their support in this program. Messrs. James C. Sivells and :Hartley A. Soul; were mecia1 technical consultan
15、ts on this Droject and Mr. Ron Anton was computer consultant. V Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-l- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CONTENTS Page SUMMARY iii FOREWORD .
16、V LIST OF ILLUSTRATIONS viii LIST OF TABLES. xi LIST OF SYMBOLS. . xiii SECTION 1 INTRODUCTION. 1 SECTION 2 BASIC CONSIDERATIONS OF AIRPLANE STAUING. 4 SECTION 3 THEORETICAL ANALYSI S. 21 SECTION 4 COMPUTER PROGRAM. 42 SECTION 5 PARAMETRIC INVESTIGATION . 75 SECTION 6 SCALE MODEL WIND TUNNEL TESTING
17、. . 131 SECTION 7 DESIGN PROCEDURES. . 136 SECTION 8 CONCLUSIONS AND RECOMMENDATIONS 142 SECTION 9 REFERENCES . 144 APPENDIX A INTERNAL LISTING OF THE COMPUTER PROGRAM 149 vii II I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ILLUSTRATIONS Figure
18、Page 1 Representative Lift Curve (Reproduced from Reference 13) . 10 2 Th.e Low-Speed Stalling Characteristics of Airfoil Sections Correlated With. Reynolds Number and the Upper-Surface Ordinates of the Airfoil Sections at the 0.0125-Chord Station . 12 Wing Leading Edge Mofifications for Controlling
19、 Wing Stall . 20 Definition of Parameters for Transformation of Wing-Body Combinat ion. 26 Typical Load Distributions for Obtaining Factors for Altering Two-Dimensional Data . 37 Illustration of Meth.od for Correcting Two- Dimensional Section Data . 39 Extrapolations of Lift Curve Slopes at Low Reyn
20、olds Number 51 Variation of Section Lift-Curve Slope with Thick- ness-Chord Ratio at Constant Reynolds Number NACA 644 Sections 54 9 Corrected Lift Curves for NACA 64-421 Airfoil at Low Reynolds Numbers 55 10 Method of Tabulation of Section Ch.aracteristics . . 57 11 Sch.ematic Representation of Sec
21、tion Data Storage 12 Nomenclature for Developing Interpolation Formulae 61 in the Computer 59 13 Computer Program Block Diagram . 62 1.4 Schematic Representation of the Computer Input Cards 63 15 Experimental and Calculated Characteristics for a Wing of Aspect Ratio 8.04 68 viii Provided by IHSNot f
22、or ResaleNo reproduction or networking permitted without license from IHS-,-,-li- - J Page Figure 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Experimental and Calculated Characteristics for a Wing of Aspect Ratio 10.05 . 70 Experimental and Calculated Characteristics for a Wing of Aspect Rati
23、o 12.06 . 72 Experimental and Calculated Characteristics for Wing with. 60% Flap; Aspect Ratio 9.02; Taper Ratio 0.4; Washout 2O 74 Typical Lift Distributions Along Wing Span . 81 Variation of Clmax with Reynolds Number and Thickness-Chord Ratio 83 Variation of CLmax with Reynolds Number and Taper R
24、atio . 86 Effect of Aspect Ratio on Stall Margin Distribution . 88 Effect of Aspect Ratio on Wing Stall Pattern 91 Effect of Aspect Ratio and Taper Ratio on Lmax. . 94 Increment of Induced-Drag Coefficient Due to Washout, 230 Series Airfoil Section 98 Effect of Root Thickness-Chord Ratio on Stall Ma
25、rgin Distribution 101 Effect of Root Thickness-Chord Ratio on Wing Stall Boundaries . 104 Effect of Root Th,ickness-Chord Ratio on CLmax . , . 107 Effect of Tip Thickness-Chord Ratio on Stall Margin Distribution 111 Effect of Tip Thickness-Chord Ratio on Lmax . 114 Effect of Reynolds Number on Stall
26、 Margin Distribution . 117 Effect of Reynolds Number on Wing Stall Pattern 120 ix Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure Page 33 Effect of Reynolds Number on Ch ax. 123 34 Effect of Wing Camber on Stall Margin Distribution. 127 35 Eff
27、ect of Fuselage . 128 on the Wing Stalling Characteristics. 130 36 Effect of the Span of a 20% Chord Split Flap 37 Variation of Wing Maximum Lift Coefficient with. Stall Speed . 138 X Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLES Tables I I1
28、 I11 Page Airfoil Section Data Available for Use with the Computer Program 56 Typical Computer Output . 65 Summary of Configurations Studied . 76 xi Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or netwo
29、rking permitted without license from IHS-,-,-A A Ai An a al Di CL SYMBOLS non-dimensional fuselage semil5eigh.t fuselage semih.eight , f t . wing aspect ratio, coefficients in trigonometric series non-dimensional average distance of point on wing from fuselage cross-section focI-1 average distance o
30、f point on wing from fuselage cross-section focii, ft. section lift-curve slope, per degree non-dimensional fuselage semiwidth fuselage semiwidth, ft. wing span, ft. flap span, ft. total wing drag coefficient,- D qs wing profile drag coefficient, qs wing induced drag coefficient,- Di qs wing lift co
31、efficient, - L qs wing pitching moment coefficient, total section drag coefficient section induced drag coefficient section profile drag coefficient section lift coefficient, - M I qc Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-c12 C C CR CT D DO
32、 Di E e design lift coefficient two-dimensional, uncorrected value of lift coefficient maximum section lift coefficient maximum two-dimensional section lift coefficient section lift coefficient at end of flap section lift coefficient for th.at part of lift distribution involving no discontinuity in
33、angle of attack section lift coefficient for part of lift distribution due to discontinuity in angle of attack section lift-curve slope, per degree section lift coefficient with deflected flaps, calculated assuming linear lift curves section pitching moment coefficient section pitching moment coeffi
34、cient about quarter-chord point wing chord at any spanwise station, ft. wing mean aerodynamic chord, ft. wing root chord, ft. wing tip chord, ft. total wing drag, lbs. wing profile drag, lbs. wing induced drag, lbs. edge velocity factor non-dimensional eccentricity of fuselage cross-section xiv Prov
35、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-el F FF Gmk G the aerodynamic charac- teristics of complete wings at high Reynolds number (Reference 7); the characteristics of a large number of complete airplanes (Reference 8); and compressibility effect
36、s on maximum lift (Ref- erence 9). Certain portions of the wind tunnel test data have direct design applications, oth.er portions provide a basis on which to evaluate the applicability of new th.eories, and still other portions provide information on which. to base empirical design guidance. The fli
37、ght test results provide a comprehensive evaluation of the integrated effect of all the factors that contribute to the airplane flying qualities. Measurement of the flight ch.arac- teristics of many airplanes of different types has permitted a definition of those characteristics which provide for go
38、od flying qualities. Additionally, the flight test results provide a ref- erence base for th.e correlation of th.eoretica1 prediction and wind tunnel experimental results. Much of the research. effort referenced above was accomplished and the results were published in numerous isolated reports, duri
39、ng and shortly after the end of World War 11. Immediately after this period, interest in the problems of straight wing air- craft was diverted to the pressing problems of supersonic mili- tary aircraft incorporating swept wing configurations. In general, unswept (straight) wing technology is not app
40、licable to swept wing configurations. Consequently, the wealth of information pertaining to the maximum lift and stalling of unswept wing air- craft has not previously been coordinated and hence h.as not re- ceived adequate attention. Nevertheless, in the general aviation field, interest st ill cent
41、ers on ,subsonic aircraft incorporating unswept wing configurations. A need therefore exists for the application of available unswept wing stall technology to th.e design of such aircraft. This report presents a comprehensive bibliography of prior work in th.e field, and, insofar as practicable, pre
42、sents the most pertinent information in a form suitable for design application. In the preparation of this report a comprehensive review h.as been conducted of all pertinent literature alth.ough. no attempt is made to synopsize each. of th.e reports under one section. Effort h.as been made, however,
43、 to incorporate the information gained from this extensive review into design guidance procedures, recommen- dations, cautions, etc. Based on this comprehensive review of pertinent literature a math.ematica1 model was formulated and programmed for the CDC 6600 digital computer. The computer which. e
44、mploys available nonlinear wing section ch.aracteristics can be utilized to predict maximum lift and th.e spanwise load distribu- tion of a wing with. or with.out fuselage. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I As a result of this study
45、 it can be concluded that design for good airplane stalling characteristics is still part art and part science. It appears obvious, however, that application of the probability of obtaining satisfactory stalling characteristics or, at least, may yield an airplane design wh.ose characteristics can be
46、 made acceptable as the result of minor modifications during early flight test phase. i the available knowledge in early design stage will greatly improve I 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SECTION 2 BASIC CONSIDERATIONS OF AIRPLANE
47、STALLING 2.1 MINI“ REQUIREMENTS FOR ACCEPTABLE STALL CHARACTERISTICS The MINIMUM REGULATORY requirements for the stalling behavior of small aircraft are stated in the Federal Aviation Regulations, Part 23 “Airworthiness Standards: Normal, Utility and Acrobatic Category Airp1.anes (Reference 10). Wit
48、h. the legalistic qualif- ications deleted, the regulations require that for specified power, gear and flap settings acceptable stalling characteristics be demonstrated for two f1igh.t maneuvers, one in straight flight with the wings level and one in a coordinated turn. In both cases the primary control manipulation is a
