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Dec 13th, 2021
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  1.  
  2. airBrake = 1; /// does aircraft has airbrake 0/1 [no/yes]
  3. airBrakeFrictionCoef = 2.4;
  4. flaps = 1; /// does aircraft uses flaps 0/1 [no/yes]
  5. flapsFrictionCoef = 0.36; /// sets the effectivity of using flaps to increase drag/lift
  6. gearsUpFrictionCoef = 0.8;
  7. brakeDistance = 250; /// braking distance
  8. wheelSteeringSensitivity = 4; /// wheel stearing sensativity on ground
  9. maxSpeed = 1800; /// max speed kmh
  10. RHS_AfterBurner_MaxSpeed = 2000;
  11. RHS_AfterBurner_Boost = 0.18;
  12. RHS_AfterBurner_FuelDrag = 0.19;
  13. altFullForce = 5000; /// CRUISE ALTITUDE
  14. altNoForce = 15000; /// SERVICE CEILING
  15. rudderInfluence = 0.7660; /// Basic angle (cos angle) of the rudder extent
  16. noseDownCoef = 0;
  17.  
  18. aileronSensitivity = 1.2; /// coefficient of ailerons affecting roll of the plane
  19. elevatorSensitivity = 1.4; /// coefficient of elevators affecting changing of plane horizontal heading
  20.  
  21. elevatorControlsSensitivityCoef = 4.0; /// elevator coefficient of player's controller sensitivity (does not affect AI)
  22. aileronControlsSensitivityCoef = 3.5; /// aileron coefficient of player's controller sensitivity (does not affect AI)
  23. rudderControlsSensitivityCoef = 4.0; /// rudder coefficient of player's controller sensitivity (does not affect AI)
  24.  
  25. /// envelope defines lift produced by the shape of the plane according to current speed relative to maxSpeed
  26. /// the first element of the array is for zero speed, the last for 125 % of maxSpeed, the rest in between is evenly distributed
  27. /// there may be as many elements as you wish, using 13 should be preferred as it modulates the 10% increase with reasonable error
  28. /// this setting is linked to geometry LOD in the model, and usees the weight data from GEO LOD
  29. envelope[] =
  30. {
  31. 0, // 0
  32. 0.11, // 100
  33. 0.83, // 200
  34. 1.97, // 300
  35. 2.42, // 400
  36. 2.69, // 500
  37. 3.87, // 600
  38. 5.27, // 700
  39. 6.89, // 800
  40. 8.72, // 900
  41. 9.7, // 1000
  42. 9.6, // 1100
  43. 9.2, // 1200
  44. 8.5, // 1300
  45. 8.2, // 1400
  46. 8.0 // 1500
  47. };
  48.  
  49. /// rudder, elevator, aileron, thrust effectiveness; if empty old settings is used
  50. /// effectiveness according to current speed and maxSpeed ratio
  51. /// last value goes for 150% of max speed
  52. thrustCoef[] =
  53. {
  54. 1.76, // 0
  55. 1.69, // 120
  56. 1.62, // 240
  57. 1.68, // 360
  58. 1.74, // 480
  59. 1.81, // 600
  60. 1.89, // 720
  61. 1.95, // 840
  62. 1.96, // 960
  63. 1.96, // 1080
  64. 1.92, // 1200
  65. 1.4, // 1320
  66. 0.4, // 1440
  67. 0.0, // 1560
  68. 0.0, // 1680
  69. 0.0 // 1800
  70. }; /// default value is 1
  71. elevatorCoef[] =
  72. {
  73. 0.3, // 0
  74. 0.50, // 120
  75. 0.66, // 240
  76. 0.52, // 360
  77. 0.49, // 480
  78. 0.46, // 600
  79. 0.43, // 720
  80. 0.40, // 840
  81. 0.35, // 960
  82. 0.30, // 1080
  83. 0.25, // 1200
  84. 0.18, // 1320
  85. 0.17, // 1440
  86. 0.16, // 1560
  87. 0.15, // 1680
  88. 0.15 // 1800
  89. }; /// default value is 1
  90. aileronCoef[] =
  91. {
  92. 0.4, // 0
  93. 0.5, // 120
  94. 0.8, // 240
  95. 0.95, // 360
  96. 1.02, // 480
  97. 1.04, // 600
  98. 1.03, // 720
  99. 1.01, // 840
  100. 1.0, // 960
  101. 0.7, // 1080
  102. 0.6, // 1200
  103. 0.55, // 1320
  104. 0.5, // 1440
  105. 0.45, // 1560
  106. 0.4, // 1680
  107. 0.35 // 1800
  108. }; /// default value is 1
  109. rudderCoef[] =
  110. {
  111. 0.5, // 0
  112. 1.8, // 120
  113. 2.6, // 240
  114. 2.75, // 360
  115. 2.8, // 480
  116. 2.85, // 600
  117. 2.9, // 720
  118. 2.95, // 840
  119. 2.98, // 960
  120. 3.01, // 1080
  121. 2.7, // 1200
  122. 1.1, // 1320
  123. 0.9, // 1440
  124. 0.7, // 1560
  125. 0.5, // 1680
  126. 0.3 // 1800
  127. }; /// default value is fabs(speed.Z())*InvSqrt(Square(speed.X())+Square(speed.Z()));
  128.  
  129.  
  130. //angleOfIndicence = __EVAL(-1.0*3.1415/180); // angle of incidence - difference between forward and airfold chord line - def. val is 3*PI/180 (meaning three degrees), be carefull with this value, will affect how much the nose of aircraft drops down during a level flight
  131. angleOfIndicence = 0.04; // angle of incidence - difference between forward and airfold chord line - def. val is 3*PI/180 (meaning three degrees), be carefull with this value, will affect how much the nose of aircraft drops down during a level flight
  132. draconicForceXCoef = 8.0; // yaw axis
  133. draconicForceYCoef = 1.2; // pitch axis
  134. draconicForceZCoef = 1.0; // ???
  135. draconicTorqueXCoef[] =
  136. {
  137. 4.0, // 0
  138. 5.1, // 180
  139. 6.1, // 360
  140. 7.0, // 540
  141. 7.7, // 720
  142. 8.3, // 900
  143. 9.0, // 1080
  144. 9.1, // 1260
  145. 9.2, // 1440
  146. 9.2, // 1620
  147. 9.2 // 1800
  148. };
  149. draconicTorqueYCoef[] =
  150. {
  151. 6.8, // 0
  152. 5.5, // 75
  153. 4.0, // 150
  154. 1.5, // 225
  155. 0.1, // 300
  156. 0.0, // 375
  157. 0.0, // 450
  158. 0.0, // 525
  159. 0.0, // 600
  160. 0.0, // 675
  161. 0.0, // 750
  162. 0.0, // 825
  163. 0.0, // 900
  164. 0.0, // 975
  165. 0.0, // 1050
  166. 0.0, // 1125
  167. 0.0, // 1200
  168. 0.0, // 1275
  169. 0.0, // 1350
  170. 0.0, // 1425
  171. 0.0, // 1500
  172. 0.0, // 1575
  173. 0.0, // 1650
  174. 0.0, // 1725
  175. 0.0 // 1800
  176. };
  177.  
  178. airFrictionCoefs0[] = { 0.0, 0.0, 0.0 };
  179. airFrictionCoefs1[] = { 0.1, 0.5, 0.0075 };
  180. airFrictionCoefs2[] = { 0.001, 0.005, 0.000067};
  181. /// FM imformation for AI
  182. landingSpeed = 275; /// used for AI to approach the runawy, the plane should be stable at this speed
  183. stallSpeed = 250;
  184. stallWarningTreshold = 0.5;
  185. acceleration = 200; /// used for AI to plan the waypoints and accelerating, doesn't affect plane performance
  186. landingAoa = __EVAL(6.2*3.1415/180); /// what AoA is going the IA use to land the plane
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