NASA-CR-3664-1983 Development of aerodynamic prediction methods for irregular planform wings《不规则平面机翼的空气动力学预测方法发展》.pdf

1、NASA Contractor Report 3664 Development of Aerodynamic Prediction Methods for Irregular Planform Wings David B. Benepe, Sr. CONTRACT NASl-15073 FEBRUARY 198 3 . . Nnsn LOAN COPY:RETUR? TO AFWLTECliNICAL LIBiihRi KJRTIANDAFB, KM. Provided by IHSNot for ResaleNo reproduction or networking permitted wi

2、thout license from IHS-,-,-TECH LfBFtARY KAFB, NM NASA Contractor Report 3664 Development of Aerodynamic Prediction Methods for Irregular Planform Wings David B. Benepe, Sr. General Dynamics Fort Worth, Texas Prepared for Langley Research Center under Contract NAS l- 15 0 7 3 NASA National Aeronauti

3、cs and Space Administration Scientific and Technical Information Branch 1983 OOb2467 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE OF CONTENTS L

4、IST OF TABLES LIST OF FIGURES SUMMARY INTRODUCTION LIST OF SYMBOLS LE = 25 , TE : 25 31 Wing II; LE = 35, TE = 20 32 Wing III; LE = 45, TE = 15 33 Wing IV; LE = 53, TE = 7O 34 Wing V; LE = 60, TE = 0 35 Sketch showing general arrangement of model used in investigation 36 Wing Planform Geometry Defin

5、itions 38 Body Geometry 46 Early Analysis Approach 66 Recent Potential Flow (Lifting Surface Theory) Analysis 66 Analysis Including Effect of Vortex Flow 66 Calculation Chart for Prediction of Nonlinear Lift of Double-Delta Planforms at Subsonic Speeds 67 Comparison of Spencer CLaPrediction With Tes

6、t Data 67 Effect of Outboard-Panel Sweep on Lift 68 Effect of Outboard-Panel Sweep on Lift ata= 16O 68 . . . VIII Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure 12. Figure 13. Figure 14. Figure 15. Figure 16. Figure 17. Figure 18. Figure 19.

7、Figure 20. Figure 21. Figure 22. Figure 23. LIST OF FIGURES (Contd.) Page WINSTAN Nonlinear Predictions for Wing I Planforms (Sharp Thin Airfoils) Effect of Fillet Sweep on Lift of Wing I Planforms ata= 16O Effect of Round Leading Edges on Vortex Lift at a = 16 Correlation of Lift Curves of Gothic a

8、nd Ogee Plan- forms Effect of Outbogrd Panel on Peckham-Type CL Corre- lation (AF = 80 ) Effect of Outbogrd Panel on Peckham-Type CL Corre- lation (hF = 75 ) Effect of Inbgard Panel on Peckham-Type CL Correla- tion a, = 25 ) Modified Peckham Correlation for SHIPS Wing I Plan- forms Ericsson Version

9、of Peckham Method - Area-Weighted Osine ALEeff Analysis Method for Round Leading Edges Variations of Suction Ratio With Angle of Attack for Various Reynolds Numbers Variations of Suction Ratio With Angle of Attack for Various Planforms at Unit Reynolds Number of 4.0x106/Ft 69 69 70 70 71 71 72 72 73

10、 74 74 74 ix Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-LIST OF FIGURES (Contd.) Figure 24. Figure 25. Figure 26. Figure 27. Figure 28. Figure 29. Figure 30. Figure 31. Figure 32. Figure 33. Figure 34. Figure 35. Variations of Suction Ratio With

11、 Angle of Attack Showing Effect of Fillet Prediction of Nonlinear Lift Using Test Values of Suction Ratio for Various Reynolds Numbers Prediction of Nonlinear Lift Using Test Values of Suction Ratio for Wing I With 60 Fillet Prediction of Nonlinear Lift Using Test Values of Suction Ratio for Wing I

12、With 80 Fillet Prediction of Nonlinear Lift Using Test Values of Suction Ratio for Wing V With 80 Fillet Variation of Leading-Edge-Suction Ratio With Angle of Attack - Wing I With 80 Fillet Variation of Leading-Edge-Suction Ratio With Angle of Attack - Wing I with 65 Fillet Variation of Leading-Edge

13、-Suction Ratio With Angle of Attack - Delta and Cropped Delta Wings Leading-Edge-Suction Values Calculated From Test Data - Wing III With 70 Fillet Comparisons of Predicted and Test Lift Curves - Wing III With 70 Fillet Modified Variations of Leading-Edge-Suction Ratio - Wing III With 70 Fillet Comp

14、arisons of Aeromodule Predictions With Test Data - Configuration 25 25.0008 X Page 74 75 75 75 75 76 77 78 79 80 81 82 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-LIST OF FIGURES (Cont“d.) Figure 36. Comparisons of Aeromodule Predictions With Tes

15、t Page Data - Configuration 45 45.0008 83 Figure 37. Comparisons of Aeromodule Predictions With Test Data - Configuration 60 60.0008 84 Figure 38. Comparisons of Aeromodule Predictions With Test Data - Configuration 80 25.0008 85 Figure 39. Comparisons of Aeromodule Predictions With Test Data - Conf

16、iguration 80 45.0008 86 Figure 40. Comparisons of Aeromodule Predictions With Test Data - Configuration 80 60.0008 87 Figure 41. Comparisons of Aeromodule Predictions With Test Data - Configuration 35 25.0008 88 Figure 42. Comparisons of Aeromodule Predictions With lest Data - Configuration 55 45.00

17、08 : 89 Figure 43. Comparisons of Aeromodule Predictions With Test Data - Configuration 65 60.0008 90 Figure 44. Comparison of Aeromodule Longitudinal Stability Derivative With Test Data for Wing I With Various Fillets 91 Figure 45. Minimum Drag Test-To-Theory Comparisons 92 Figure 46. Results of An

18、alysis Using Mendenhall Lifting Surface Plus Suction Analogy Computer Procedure and WINSTAN Methods 93 Figure 47. Scatter Plot Showing Spread of Lift Data for all 35 SHIPS Planforms 109 xi Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-LIST OF FIGUR

19、ES (Contd.) Page Plot Showing Spread of Lift Data for Constant Fillet Sweep 110 Example of Lift Data Collapse Using CL/CLQ,Parameter for 80 Fillet Sweep 111 Example of Lift Data Collapse Using CL/CLcrParameter for Basic SHIPS Planforms 112 Figure 48. Figure 49. Figure 50. Figure 51. Figure 52. Figur

20、e 53. Figure 54. Figure 55. Figure 56. Figure 57. Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings with 80 Fillet Sweep Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings -

21、 Wings With 75 Sweep Fillets Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings With 70 Sweep Fillets Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings With 65 Sweep

22、 Fillets Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings With 60 Sweep Fillets 113 114 115 116 117 Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings with 55 Sweep

23、 Fillets and Basic Wing IV 118 Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings With 45 Sweep Fillets 119 xii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure 58. Figure 59. F

24、igure 60. Figure 61. Figure 62. Figure 63. Figure 64. Figure 65. Figure 66. Figure 67. Figure 68. LIST OF FIGURES (Contd.) Page Correlation of SHIPS Test Data Using WINSTAN Corre- lation Parameter for Nonlinear Lift of Double-Delta Wings - Wings With 35 Sweep Fillets and Basic Wing I SHIPS Lift Data

25、 Correlation Using WINSTAN Method for Double-Delta Wings (Preliminary) Scatter Plot for Modified Peckham Lift Correlation Parameter for All 35 SHIPS Planforms Modified Peckham Correlation of Lift Data - Basic Wings Modified Peckham Correlation of Lift Data - AF = 65 Modified Peckham Correlation of L

26、ift Data - AF = 80 Data Collapse With Further Modification of Peckham Lift Correlation Parameter - Basic Wings Data Collapse With Further Modification of Peckham Lift Correlation Parameter - AF = 80 Data Collapse With Further Modificat&on of Peckham Lift Correlation Parameter - AF = 75 Data Collapse

27、 With Further Modificathon of Peckham Lift Correlation Parameter - AF = 70 Data Collapse With Further ModificatAon of Peckham Lift Correlation Parameter - AF = 65 120 121 122 123 124 125 126 127 128 129 130 . . . XIII Provided by IHSNot for ResaleNo reproduction or networking permitted without licen

28、se from IHS-,-,-LIST OF FIGURES (Contd.) Figure 69. Data Collapse With Further Modification of Peckham Lift Correlation Parameter - A, = 60 Figure 70. Data Collapse With Further Modification of Peckham Lift Correlation Parameter - AF = 55 Figure 71. Data Collapse With Further Modification of Peckham

29、 Lift Correlation Parameter - AF = 45 Figure 72. Data Collapse With Further Modification of Peckham Lift Correlation Parameter - A, = 35 Figure 73. Ratio of Actual Lift to Predicted Linear Lift of SHIPS Planforms With NACA 0008 Airfoils - Basic Wings Figure 74. Ratio of Test Lift to Predicted Linear

30、 Lift of SHIPS Planforms with NACA 0008 Airfoils-AF = 80 Figure 75. Ratio of Test Lift to Predicted Linear Liftoof SHIPS Planforms with NACA 0008 Airfoils - AF = 75 Figure 76. Ratio of Test Lift to Predicted Linear Liftoof SHIPS Planforms with NACA 0008 Airfoils - AF = 70 Figure 77. Ratio of Test Li

31、ft to Predicted Linear Liftoof SHIPS Planforms with NACA 0008 Airfoils - AF = 65 Figure 78. Ratio of Test Lift to Predicted Linear Liftoof SHIPS Planforms with NACA 0008 Airfoils - AF = 60 Page 131 132 133 134 135 136 137 138 139 140 Xiv Provided by IHSNot for ResaleNo reproduction or networking per

32、mitted without license from IHS-,-,-LIST OF FIGURES (Contd.) Figure 79. Figure 80. Figure 81. Figure 82. Figure 83. Figure 84. Figure 85. Figure 86. Figure 87. Figure 88. Figure 89. Ratio of Test Lift to Predicted Linear Lift of SHIPS Page Planforms with NACA 0008 Airfoils - AF = 55and 53 141 Ratio

33、of Test Lift to Predicted Linear Liftoof SHIPS Planforms with NACA 0008 Airfoils - AF = 45 142 Ratio of Test Lift to Predicted Linear Liftoof SHIPS Planforms with NACA 0008 Airfoils - AF = 35 143 Ratio of Test Lift to Nonlinear Potential Flow Esti- mate for Basic SHIPS Planforms 144 Ratio of Test Li

34、ft to Nonlinear Po&ential Flow Esti- mate for SHIPS Planforms Having 80 Fillets 145 Variations of Leading-Edge-Suction Ratio pith Angle of Attack for Irregular Planforms with 75 Fillet Sweep 146 Example of Angle-of-Attack Boundary Variations with Fillet Sweep for Wing I Planforms 147 Correlation of

35、Suction Ratio “R“ Using Effective Leading Edge Radius Reynolds Number 148 Correlation of Suction Ratio Using WINSTAN 0 Para- meter 149 Comparison of Correlation Curve Values of Suction Ratio with SHIPS Basic Wing Test Data Comparison of Simple Prediction Approach with Suction Ratio Data 150 151 xv P

36、rovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-LIST OF FIGURES (Contd.) Figure 90. Figure 91. Figure 92. Figure 93. Figure 94. Figure 95. Figure 96. Figure 97. Figure 98. Figure 99. Figure 100. Figure 101. Figure 102. Page Calculation Chart for Incre

37、mental Effect of Fillet Sweep on Suction Ratio in Plateau Regio Between CY= 0 and a2 152 Upper Angle-of-Attack Boundaries for Region 1 153 Incremental Angle of Attack for Region 2 154 Incremental Angle of Attack for Region 3 155 Incremental Angle of Attack for Region 4 156 Effect of Reynolds Number

38、on a3 157 Correlation of Reynolds Number Effects on “2 for Basic Wings Using Chappells Correlation Parameter 158 Correlation of Reynolds Number Effects on cx2 for Basic Wings Using Q Function Based on Leading- Edge Radius at Tip 159 Envelope Correlation Curve for Change in “2 of Basic Wings Due to C

39、hange in Reynolds Number 160 Envelope Correlation Curve for Change in a3 of Basic Wings Due to Change in Reynolds Number 161 Envelope Correlation Curve For Change in a4 of Basic Wings Due to Change in Reynolds Number 162 Envelope Correlation Curve for Change in “5 of Basic Wings Due to Change in Rey

40、nolds Number 163 Correction Term for Effect of Fillet Sweep on a Boundaries 164 xvi Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Figure 103. Figure 104. Figure 105. Figure 106. Figure 107. Figure 108. Figure 109. Figure 1lJ. Figure 111. Figure 112

41、. Figure 113. LIST OF FIGURES (Contd.) Page Aerodynamic Center Locations of SHIPS Wing I Plan- forms for Various Lift Regions 166 Aerodynamic Center Locations of SHIPS Wing II Plan- forms for Various Lift Regions 167 Aerodynamic Center Locations of SHIPS Wing III Plan- forms-for Various Lift Regions

42、 Aerodynamic Center Locations of SHIPS Wing IV Plan- forms for Various Lift Regions Aerodynamic Center Locations of SHIPS Wing V Plan- forms for Various Lift Regions Angle-of-Attack Envelope for Primary Aerodynamic Center Location Lift Coefficient Envelope for Primary Aerodynamic Center Location Aer

43、odynamic Center Prediction - Paniszczyn Method Modified by K Factor Applied to Lift of Inboard Panel - Wing I Planfonns Aerodynamic Center Prediction - Paniszczyn Method Modified by K Factor Applied to Lift of Inboard Panel - Wing II Planforms Aerodynamic Center Prediction - Paniszczyn Method Modifi

44、ed by K Factor Applied to Lift of Inboard Panel - Wing III Planforms Aerodynamic Center Prediction - Paniszczyn Method Modified by K Factor Applied to Lift of Inboard Panel - Wing IV Planforms 168 169 170 171 172 173 174 175 176 xvii Provided by IHSNot for ResaleNo reproduction or networking permitt

45、ed without license from IHS-,-,-Figure 114. Figure 115. Figure 116. Figure 117. Figure 118. Figure 119. Figure 120. Figure 121. Figure 122. Figure 123. LIST OF FIGURES (Contd.) Page Aerodynamic Center Prediction - Paniszczyn Method Modified by K Factor Applied to Lift of Inobard Planforms - Wing V P

46、lanforms Aerodynamic Center Location Referenced to Mean Geometric Chord of Each Irregular Planform Aerodynamic Center Referenced to Mean Geometric Chord of Each Basic Wing Aerodynamic Center Location Referenced to Apex of 80 Fillet for Each Planform Family Aerodynamic Center Location Referenced to A

47、pex of 80/25 Planform with Common Location of Quarter Chord of MGC of each Basic Wing Aerodynamic Center Location as a Percentage of Root Chord of Each Irregular Planform Variation of Aerodynamic Center Location Referenced to Mean Geometric Chord of Each Irregular Planform with Outer Panel Leading-E

48、dge Sweep Variation of Aerodynamic Center Location as a Per- centage of Root Chord of Each Irregular Planform with Outer Panel Leading-Edge Sweep Effect of Reynolds Number on Aerodynamic Center Location for Various Lift Regions - Wing I Plan- forms Effect of Reynolds Number on Aerodynamic Center Location for Various Lift Regions - Wing II Plan- forms 177 178 179 180 181 182 183 184 185 186 . . . xv111 Provided by IHSNot for ResaleNo reproduction or networking permitted