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Text File  |  1979-12-31  |  6KB  |  176 lines
  1. /* --------------------------------- yplane.prc ----------------------------- */
  2.  
  3. /* This is part of the flight simulator 'fly8'.
  4.  * Author: Eyal Lebedinsky (eyal@ise.canberra.edu.au).
  5. */
  6.  
  7. /* plane parameters: YPLANE
  8. */
  9.  
  10. #include "parms.h"
  11.  
  12. 15586,        /* weight [lb]                        */
  13. F10(1.38),    /* Ixx as I/Weight in kg-m2/kg                */
  14. F10(8.14),    /* Iyy                            */
  15. F10(9.20),    /* Izz                            */
  16. F10(0.14),    /* Izx                            */
  17.  
  18. 120,        /* liftoff [kts]                    */
  19. V(9*G),        /* max positive vertical acceleration            */
  20. V(-6*G),    /* max negative vertical acceleration            */
  21. DV(34),        /* pitch rate at 300kts full elevators [ang/s]        */
  22. DV(180),    /* roll rate at 300 kts full ailerons [ang/s]        */
  23. V(1.00),    /* height   (eye above cg)                */
  24. V(3.00),    /* position (eye forward of cg)             */
  25. D(-1),        /* onground pitch [ang]                    */
  26. 50000,        /* ceiling [ft]                        */
  27. 511,        /* stores: M61                        */
  28. 0,        /* stores: MK82                        */
  29. 0,        /* stores: spare                    */
  30. 0,        /* stores: spare                    */
  31. 0,        /* stores: spare                    */
  32.  
  33. F(0.70),    /* friction with brakes applied                */
  34. F(0.02),    /* friction when freewheeling                */
  35.  
  36. I10(18000),    /* thrust (mil) [lbf]                    */
  37. 71,        /* sfc (mil)                        */
  38. I10(29588),    /* thrust (ab) [lbf]                    */
  39. 217,        /* sfc (ab)                        */
  40. 6846,        /* fuel capacity [lb]                    */
  41. D(0),        /* Engine rigging angle vs. plane            */
  42. D(0),        /* Engine offset angle vs. plane            */
  43. V(0),        /* Engine offset vs. cg                    */
  44.  
  45. V(27.87),    /* wings area [vm]                    */
  46. V(10),        /* wing span, tip to tip [vm]                */
  47. V(3.5),        /* cbar, mean aerodynamic cord [vm]            */
  48. V( 0.00),    /* wing ac offset forward of cg                */
  49. V( 0.00),    /* wing ac offset above cg                */
  50. D(0),        /* Wing rigging angle vs. plane (+=leading edge high)    */
  51. D(0),        /* alpha where Cl=0                    */
  52. F10( 2.0),    /* max Cl for wing foil                    */
  53. F10(-1.5),    /* min Cl for wing foil                    */
  54. F(-8.0/20.0),    /* flaps effective alpha/flaps                */
  55. F(0.4/D(20)),    /* flaps ClMax rate/Flaps [1/ang]            */
  56. F(1.0/D(25)),    /* LE flaps ClMax rate/Flaps [1/ang]            */
  57. 93,        /* efficiency                        */
  58. F(-0.004),    /* Cm0w of wing                        */
  59.  
  60. V(5.92),    /* tail area                        */
  61. V(5.58),    /* tail span                        */
  62. V(-3.00),    /* tail a.c. offset forward of c.g.            */
  63. V( 0.00),    /* tail a.c. offset above c.g.                */
  64. D(-2.5),    /* Tail rigging angle vs. wing (+=leading edge high)    */
  65. F(0.60),    /* tail volume                        */
  66. F10(1.5),    /* tail max Cl                        */
  67. F10(-1.5),    /* tail min Cl                        */
  68.  
  69. V(5.09),    /* rudder area                        */
  70. V(3.0),        /* rudder span                        */
  71. V(-3.00),    /* rudder a.c. offset forward of c.g.            */
  72. V( 0.00),    /* rudder a.c. offset above c.g.            */
  73. F10(1.5),    /* rudder max Cl (symmetrical)                */
  74.  
  75. F(0.05),    /* parasitic drag: profile                */
  76. F(0.50),    /* parasitic drag: speed brakes                */
  77. F(0.10),    /* parasitic drag: gear                    */
  78. F(0.002),    /* parasitic drag: each MK82                */
  79.  
  80. D(20),        /* max flaps [ang]                    */
  81. D(25),        /* max leFlaps [ang]                    */
  82. D(40),        /* max spoilers [ang]                    */
  83. D(25),        /* max elevators [ang]                    */
  84. D(21.5),    /* max ailerons [ang]                    */
  85. D(30),        /* max rudder [ang]                    */
  86.  
  87. D(10),        /* AutoFlaps: min aoa to engage                */
  88. F(100.0/D(15)),    /* AutoFlaps: flaps/aoa rate                */
  89. 50,        /* AutoFlaps: max flaps authority (%)            */
  90.  
  91. D(15),        /* AutoLEFlaps: min aoa to engage            */
  92. F(100.0/D(15)),    /* AutoLEFlaps: leFlaps/aoa rate            */
  93.  
  94. V(120.0),    /* AutoElevators: speed factor.                */
  95.  
  96. V(10.0),    /* AutoPedals: speed factor.                */
  97.  
  98. F( 0.20),    /* Cydr    rudder sideforce                */
  99. F10(-2.00),    /* Cybeta vx damping                    */
  100.  
  101. F( 0.04),    /* Cm0    of whole plane                    */
  102. F(-0.30),    /* Cmde    elevators effectiveness                */
  103. F10(-8.00),    /* Cmq    pitch damping                    */
  104. F(-0.40),    /* Cmalpha wing/stabilizer induced pitch        */
  105. F10(-2.0),    /* Cmalphadot alpha rate induced pitch            */
  106.  
  107. F( 0.15),    /* Clda    ailerons effectiveness                */
  108. F(-0.60),    /* Clp    roll damping                    */
  109. F(-0.10),    /* Clbeta dihedral effect                */
  110. F( 0.00),    /* Cldr    roll from rudder                */
  111.  
  112. F(-0.05),    /* Cndr    rudder effectiveness                */
  113. F(-1.00),    /* Cnr    yaw damping                    */
  114. F( 0.10),    /* Cnbeta weathercock stability                */
  115. F(-0.01),    /* Cnda    ailerons induced yaw (negative = adverse)    */
  116. F( 0.00),    /* Cnp    roll induced yaw                 */
  117.  
  118. HUD_F16,    /* HUD style                        */
  119.  
  120. /* these 10 options are for future use.
  121. */
  122.     MODEL_YPLANE,    /* flight dynamics model            */
  123.     2,        /* response (larger means slower)        */
  124.     0,        /* reserved                    */
  125.     0,        /* turn speed (classic), lift (basic)        */
  126.     0,        /* reserved                    */
  127.     -1,        /* c.g. height (calculated)            */
  128.     0,        /* reserved                    */
  129.     0,        /* reserved                    */
  130.     0,        /* reserved                    */
  131.     0,        /* reserved                    */
  132.  
  133.  
  134. /* these are the three autopilot PID parameter sets.
  135.  *
  136.  *        P,    Iband, Ki,    Dband, Kd,     factor,    limit
  137. */
  138. /* throttle */    400,    V(0.02), 10,    V(0.05), 400,     1000*VONE,     20,
  139. /* pitch    */     40,    D(2), 100,    D(10), 100,     100*D90/50,     40,
  140. /* roll     */    300,    D(10), 10,    D(90), 300,    -100*D90/50,    100,
  141.  
  142.  
  143. /* Landing gear parameters. Up to 5 gear assemblies can be defined.
  144.  *
  145.  * x    gear tip position right of cg
  146.  * y    gear tip position forward of cg
  147.  * z    gear tip position above cg
  148.  * dgmax max gear depression.
  149.  * dtp    type depression at load P
  150.  * P    gear precharge
  151.  * Cv    gear damping
  152.  * Steer angle at max pedals
  153.  * ur    friction coeff when free rolling
  154.  * ub    friction coeff when braking
  155.  * us    friction coeff of side sliding
  156.  *
  157.  *         x          y          z         dgmax     dtp       P
  158.  *        Cv        Steer  ur       ub       us       raise lower
  159. */
  160. /* nose  */  VV(0.00),  VV(3.00), -VV(2.30), VV(1.00), VV(0.10), V(G/20),
  161.         V( 2*G),  D(40), F(0.02), F(0.00), F(0.60),  20,   25,
  162.  
  163. /* left  */ -VV(1.58), -VV(1.00), -VV(2.00), VV(0.75), VV(0.10), V(G/10),
  164.         V(   G),  D(0),  F(0.02), F(0.65), F(0.60),  20,   25,
  165.  
  166. /* right */  VV(1.58), -VV(1.00), -VV(2.00), VV(0.75), VV(0.10), V(G/10), 
  167.         V(   G),  D(0),  F(0.02), F(0.65), F(0.60),  20,   25,
  168.  
  169. /*       */  VV(0.00),  VV(0.00),  VV(0.00), VV(0.00), VV(0000), V(0.00),
  170.         V(0.00),  D(0),  F(0.00), F(0.00), F(0.00),   0,    0,
  171.  
  172. /*       */  VV(0.00),  VV(0.00),  VV(0.00), VV(0.00), VV(0000), V(0.00),
  173.         V(0.00),  D(0),  F(0.00), F(0.00), F(0.00),   0,    0,
  174.  
  175. 0 /* dummy EOF */
  176.