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Text File  |  2002-02-24  |  24.5 KB  |  1,531 lines
  1. ;1/3 scale pitts special
  2. ;2.16m wing span
  3. ;1.281 sq meters 
  4. ;It weights 33.6 kgs Its powered by a Quadra Q100B 
  5. ;7000rpm max, with 28-10 prop
  6. [Main]
  7. ShortTitle=Pitts Special Biplane
  8. ThumbnailFile=pitts.bmp
  9. Description1=Pitts Special Biplane
  10. Description2=1/3 scale, 2.16 meter span, 13.6 kg
  11. Description3=power: Quadra Q100B with 28x10 prop
  12. Author=Transcendental Technologies
  13. EmailAddr=ttransce@bigpond.net.au
  14. Website=http://www.users.bigpond.net.au/atv/preflight001.htm
  15. ;Lifetime in seconds,0 means indefinite (default)
  16. MaxLifeTime=0
  17. MaxEyeDist=50
  18. ZoomViewDistance=2.5
  19. QPPageNumber=0
  20.  
  21. [ScreenDisplays]
  22. ;DispThrottle
  23. ;DispAileron
  24. ;DispRudder
  25. ;DispElevator
  26. ;DispCollective
  27. DispAlt
  28. Speed
  29. FPS
  30. DispDistance
  31.  
  32. [Speed]
  33. Format="Speed:%.2f "
  34. Value=dist3d(_SpeedX,_SpeedY,_SpeedZ)
  35.  
  36. [FPS]
  37. Format="FPS:%.1f "
  38. Value=1/_Tick
  39.  
  40. [DispAlt]
  41. Format="Alt:%.2f "
  42. Value=_LocationY
  43.  
  44. [DispThrottle]
  45. Format="T:%.2f "
  46. Value=(1-_Throttle)
  47.  
  48. [DispAileron]
  49. Format="A:%.2f "
  50. Value=_Aileron
  51.  
  52. [DispRudder]
  53. Format="R:%.2f "
  54. Value=(1-_Rudder)
  55.  
  56. [DispElevator]
  57. Format="E:%.2f "
  58. Value=_Elevator
  59.  
  60. [DispCollective]
  61. Format="C:%.2f "
  62. Value=_Aux1
  63.  
  64. [DispDistance]
  65. Format="Distance:%f "
  66. Value=_Distance
  67.  
  68. ;Main Loop Start
  69. ;Calculation proceeds from this order:
  70.  
  71. ;Quick Parameters can be set up for anything you want to modify - quick!
  72. ; max pages=30, max parms per page = 12 if you need more than 12
  73. ; make a page called "Longpage(2)" and continue.  Use SortName parameter
  74. ; to control sequence within page.
  75. [QuickParameters]
  76. QMisSmo
  77. QSEnVol
  78. QProDia
  79. QProAre
  80. QSKDCOF
  81. QSKDDir
  82. QMaxAil
  83. QMaxRud
  84. QMaxEle
  85. QTrmAil
  86. QTrmEle
  87. QTrmRud
  88. QRudAre
  89. QEleAre
  90. QAilAre
  91. QVBdAre
  92. QEngRPM
  93. QMasTnk
  94. QMasEcn
  95. QMasSrv
  96. QMasBat
  97. QMasTai
  98.  
  99. [QMasTai]
  100. TabName=Mass Distribution
  101. Prompt=Tail Assembly (kilograms)
  102. DefaultValue=1.0
  103. CurrentValue=1.000000
  104.  
  105. [QMasBat]
  106. TabName=Mass Distribution
  107. Prompt=Batteries and Receiver (kilograms)
  108. DefaultValue=0.150
  109. CurrentValue=0.150000
  110.  
  111. [QMasSrv]
  112. TabName=Mass Distribution
  113. Prompt=Servos (kilograms)
  114. DefaultValue=0.225
  115. CurrentValue=0.225000
  116.  
  117. [QMasEcn]
  118. TabName=Mass Distribution
  119. Prompt=Engine (kilograms)
  120. DefaultValue=2.95
  121. CurrentValue=2.950000
  122.  
  123. [QMasTnk]
  124. TabName=Mass Distribution
  125. Prompt=Tank (kilograms)
  126. DefaultValue=1.8
  127. CurrentValue=1.800000
  128.  
  129. [QMisSmo]
  130. TabName=Effects
  131. Prompt=Smoke effects: 1 for smoke, 0 for healthy
  132. DefaultValue=1.0
  133. CurrentValue=1.000000
  134.  
  135. [QSEnVol]
  136. TabName=Sound
  137. Prompt=Engine Sound Volume (0 - 20000)
  138. DefaultValue=10000
  139. CurrentValue=10000.000000
  140.  
  141. [QProDia]
  142. TabName=Prop
  143. Prompt=Diameter
  144. DefaultValue=0.7112
  145. CurrentValue=0.711200
  146.  
  147. [QProAre]
  148. TabName=Prop
  149. Prompt=Area (sq.meters)
  150. DefaultValue=0.00533
  151. CurrentValue=0.005330
  152.  
  153. [QSKDCOF]
  154. TabName=Landing Gear
  155. Prompt=Coefficient of Friction
  156. DefaultValue=0.0005
  157. CurrentValue=0.000500
  158.  
  159. [QSKDDir]
  160. TabName=Landing Gear
  161. Prompt=Directionality (0 for skids, 1 for wheels)
  162. DefaultValue=1.0
  163. CurrentValue=1.000000
  164.  
  165. [QMaxAil]
  166. TabName=Controls
  167. Prompt=Total Aileron Deflection (Degrees)
  168. DefaultValue=50.0
  169. CurrentValue=50.000000
  170.  
  171. [QMaxRud]
  172. TabName=Controls
  173. Prompt=Total Rudder Deflection (Degrees)
  174. DefaultValue=50.0
  175. CurrentValue=50.000000
  176.  
  177. [QMaxEle]
  178. TabName=Controls
  179. Prompt=Total Elevator Deflection (Degrees)
  180. DefaultValue=50.0
  181. CurrentValue=50.000000
  182.  
  183. [QRudAre]
  184. TabName=Controls
  185. Prompt=Rudder Area (sq. meters)
  186. SortName=z3
  187. DefaultValue=0.070
  188. CurrentValue=0.070000
  189.  
  190. [QEleAre]
  191. TabName=Controls
  192. Prompt=Total Elevator Area (sq. meters)
  193. SortName=z2
  194. DefaultValue=0.05874
  195. CurrentValue=0.058740
  196.  
  197. [QAilAre]
  198. TabName=Controls
  199. Prompt=Total Aileron Area (sq. meters)
  200. SortName=z1
  201. DefaultValue=0.28192
  202. CurrentValue=0.281920
  203.  
  204. [QVBdAre]
  205. TabName=Body
  206. Prompt=Frontal Area (sq.meters)
  207. DefaultValue=0.185
  208. CurrentValue=0.185000
  209.  
  210. [QTrmAil]
  211. TabName=Trim
  212. Prompt=Aileron (Degrees)
  213. DefaultValue=0.0
  214. CurrentValue=0.000000
  215.  
  216. [QTrmEle]
  217. TabName=Trim
  218. Prompt=Elevator (Degrees)
  219. DefaultValue=0.0
  220. CurrentValue=0.000000
  221.  
  222. [QTrmRud]
  223. TabName=Trim
  224. Prompt=Rudder (Degrees)
  225. DefaultValue=0.0
  226. CurrentValue=0.000000
  227.  
  228. [QEngRPM]
  229. TabName=Engine
  230. Prompt=Maximum RPM
  231. DefaultValue=7000
  232. CurrentValue=7000.000000
  233.  
  234. [UserVariables]
  235. Smoker
  236. MakePuff1
  237. MakePuff2
  238. RotorYPos
  239. SlowRotorYPos
  240.  
  241. [Smoker]
  242. InitialValue=0
  243. Value=if(Smoker>0.05,0,Smoker+(_Tick*QMisSmo))
  244.  
  245. [MakePuff1]
  246. InitialValue=0.0
  247. Value=if(Smoker>0.02,spawn(10,-0.06,0.21,-0.02,0.0,-0.94,-0.342,0,0,0,0,0,0),1)
  248.  
  249. [MakePuff2]
  250. InitialValue=0.0
  251. Value=if(Smoker>0.02,spawn(10,+0.06,0.21,-0.02,0.0,-0.94,-0.342,0,0,0,0,0,0),1)
  252.  
  253. [RotorYPos]
  254. InitialValue=1.0
  255. Value=RotorYPos-(_Tick*900)        
  256.  
  257. [SlowRotorYPos]
  258. InitialValue=1.0
  259. Value=SlowRotorYPos-((_Tick*200)*((1-_Throttle)*10)
  260.  
  261. [Functions]
  262. CLTableProp
  263. CDTableProp
  264. CLTableWing
  265. CDTableWing
  266.  
  267. ;CL of eppler e854 (prop)
  268. ;RN=300000
  269. [CLTableProp]
  270. Type=Table
  271. DefaultValue=0.0
  272. NumberOfParameters=1
  273. NumberOfPoints=31
  274. X01=-90
  275. Y01=-0.02
  276. X02=-50
  277. Y02=-0.05
  278. X03=-35
  279. Y03=-0.11
  280. X04=-30
  281. Y04=-0.15
  282. X05=-25
  283. Y05=-0.24
  284. X06=-20
  285. Y06=-0.37
  286. X07=-18
  287. Y07=-0.43
  288. X08=-16
  289. Y08=-0.48
  290. X09=-14
  291. Y09=-0.50
  292. X10=-12
  293. Y10=-0.48
  294. X11=-10
  295. Y11=-0.40
  296. X12=-8
  297. Y12=-0.27
  298. X13=-6
  299. Y13=-0.10
  300. X14=-4
  301. Y14=-0.11
  302. X15=-2
  303. Y15=-0.35
  304. X16=0
  305. Y16=0.59
  306. X17=2
  307. Y17=0.82
  308. X18=4
  309. Y18=1.06
  310. X19=6
  311. Y19=1.00
  312. X20=8
  313. Y20=1.07
  314. X21=10
  315. Y21=1.06
  316. X22=12
  317. Y22=0.96
  318. X23=14
  319. Y23=0.82
  320. X24=16
  321. Y24=0.67
  322. X25=18
  323. Y25=0.54
  324. X26=20
  325. Y26=0.43
  326. X27=25
  327. Y27=0.25
  328. X28=30
  329. Y28=0.16
  330. X29=35
  331. Y29=0.11
  332. X30=50
  333. Y30=0.05
  334. X31=90
  335. Y31=0.03
  336.  
  337. ;CD of eppler e854 (prop)
  338. ;RN=300000
  339. [CDTableProp]
  340. Type=Table
  341. DefaultValue=0.0
  342. NumberOfParameters=1
  343. NumberOfPoints=31
  344. X01=-90
  345. Y01=0.6008
  346. X02=-50
  347. Y02=0.6
  348. X03=-35
  349. Y03=0.6000
  350. X04=-30
  351. Y04=0.5814
  352. X05=-25
  353. Y05=0.3724
  354. X06=-20
  355. Y06=0.2233
  356. X07=-18
  357. Y07=0.1795
  358. X08=-16
  359. Y08=0.1386
  360. X09=-14
  361. Y09=0.1089
  362. X10=-12
  363. Y10=0.0848
  364. X11=-10
  365. Y11=0.0658
  366. X12=-8
  367. Y12=0.0503
  368. X13=-6
  369. Y13=0.0403
  370. X14=-4
  371. Y14=0.0112
  372. X15=-2
  373. Y15=0.0115
  374. X16=0
  375. Y16=0.0120
  376. X17=2
  377. Y17=0.0128
  378. X18=4
  379. Y18=0.0142
  380. X19=6
  381. Y19=0.0383
  382. X20=8
  383. Y20=0.0493
  384. X21=10
  385. Y21=0.0639
  386. X22=12
  387. Y22=0.0833
  388. X23=14
  389. Y23=0.1079
  390. X24=16
  391. Y24=0.1426
  392. X25=18
  393. Y25=0.1802
  394. X26=20
  395. Y26=0.2251
  396. X27=25
  397. Y27=0.3805
  398. X28=30
  399. Y28=0.5937
  400. X29=35
  401. Y29=0.6002
  402. X30=50
  403. Y30=0.6000
  404. X31=90
  405. Y31=0.6007
  406.  
  407. ;CL of eppler e472 aerobatic
  408. ;RN=300000
  409. [CLTableWing]
  410. Type=Table
  411. DefaultValue=0.0
  412. NumberOfParameters=1
  413. NumberOfPoints=31
  414. X01=-90
  415. Y01=-0.12
  416. X02=-50
  417. Y02=-0.24
  418. X03=-35
  419. Y03=-0.48
  420. X04=-30
  421. Y04=-0.64
  422. X05=-25
  423. Y05=-0.85
  424. X06=-20
  425. Y06=-1.08
  426. X07=-18
  427. Y07=-1.16
  428. X08=-16
  429. Y08=-1.19
  430. X09=-14
  431. Y09=-1.18
  432. X10=-12
  433. Y10=-1.12
  434. X11=-10
  435. Y11=-1.00
  436. X12=-8
  437. Y12=-0.92
  438. X13=-6
  439. Y13=-0.71
  440. X14=-4
  441. Y14=-0.48
  442. X15=-2
  443. Y15=-0.24
  444. X16=0
  445. Y16=0.00
  446. X17=2
  447. Y17=0.24
  448. X18=4
  449. Y18=0.48
  450. X19=6
  451. Y19=0.71
  452. X20=8
  453. Y20=0.92
  454. X21=10
  455. Y21=1.00
  456. X22=12
  457. Y22=1.12
  458. X23=14
  459. Y23=1.18
  460. X24=16
  461. Y24=1.20
  462. X25=18
  463. Y25=1.16
  464. X26=20
  465. Y26=1.09
  466. X27=25
  467. Y27=0.85
  468. X28=30
  469. Y28=0.64
  470. X29=35
  471. Y29=0.48
  472. X30=50
  473. Y30=0.24
  474. X31=90
  475. Y31=0.17
  476.  
  477. ;CD of eppler e472 aerobatic
  478. ;RN=300000
  479. [CDTableWing]
  480. Type=Table
  481. DefaultValue=0.0
  482. NumberOfParameters=1
  483. NumberOfPoints=31
  484. X01=-90
  485. Y01=0.60006
  486. X02=-50
  487. Y02=0.6
  488. X03=-35
  489. Y03=0.5340
  490. X04=-30
  491. Y04=0.3745
  492. X05=-25
  493. Y05=0.2590
  494. X06=-20
  495. Y06=0.1592
  496. X07=-18
  497. Y07=0.1217
  498. X08=-16
  499. Y08=0.0945
  500. X09=-14
  501. Y09=0.0725
  502. X10=-12
  503. Y10=0.0535
  504. X11=-10
  505. Y11=0.0358
  506. X12=-8
  507. Y12=0.0164
  508. X13=-6
  509. Y13=0.0134
  510. X14=-4
  511. Y14=0.0133
  512. X15=-2
  513. Y15=0.0126
  514. X16=0
  515. Y16=0.0124
  516. X17=2
  517. Y17=0.0126
  518. X18=4
  519. Y18=0.0134
  520. X19=6
  521. Y19=0.0137
  522. X20=8
  523. Y20=0.0171
  524. X21=10
  525. Y21=0.0369
  526. X22=12
  527. Y22=0.0547
  528. X23=14
  529. Y23=0.0741
  530. X24=16
  531. Y24=0.0965
  532. X25=18
  533. Y25=0.1239
  534. X26=20
  535. Y26=0.1603
  536. X27=25
  537. Y27=0.2652
  538. X28=30
  539. Y28=0.3909
  540. X29=35
  541. Y29=0.5569
  542. X30=50
  543. Y30=0.6000
  544. X31=90
  545. Y31=0.6006
  546.  
  547. ;All masses:
  548.  
  549. [Masses]
  550. Engine
  551. Tank
  552. BodyN
  553. BodyS
  554. Tail
  555. MWingUL
  556. MWingUR
  557. MWingLL
  558. MWingLR
  559. ;Tail Surfaces
  560. MTailFinN
  561. MHorFinLN
  562. MHorFinRN
  563. ;Control Surfaces
  564. MElevL
  565. MElevR
  566. MRudder
  567. MAileronUL
  568. MAileronUR
  569. MAileronLL
  570. MAileronLR
  571.  
  572. [MElevL]
  573. PositionX=-0.213
  574. PositionY=0.414
  575. PositionZ=-1.235
  576. Value=0.07
  577.  
  578. [MElevR]
  579. PositionX=0.213
  580. PositionY=0.414
  581. PositionZ=-1.235
  582. Value=0.07
  583.  
  584. [MRudder]
  585. PositionX=0.0
  586. PositionY=0.479094
  587. PositionZ=-1.420
  588. Value=0.07
  589.  
  590. [MAileronUL]
  591. PositionX=-0.762
  592. PositionY=0.601
  593. PositionZ=-0.292
  594. Value=0.5
  595.  
  596. [MAileronUR]
  597. PositionX=0.762
  598. PositionY=0.601
  599. PositionZ=-0.292
  600. Value=0.5
  601.  
  602. [MAileronLL]
  603. PositionX=-0.762
  604. PositionY=0.259
  605. PositionZ=-0.292
  606. Value=0.5
  607.  
  608. [MAileronLR]
  609. PositionX=0.762
  610. PositionY=0.259
  611. PositionZ=-0.292
  612. Value=0.5
  613.  
  614. [MTailFinN]
  615. PositionX=0.0
  616. PositionY=0.479094
  617. PositionZ=-1.31281
  618. Value=0.1
  619.  
  620. [MHorFinLN]
  621. PositionX=-0.213
  622. PositionY=0.414
  623. PositionZ=-1.235
  624. Value=0.1
  625.  
  626. [MHorFinRN]
  627. PositionX=0.213
  628. PositionY=0.414
  629. PositionZ=-1.235
  630. Value=0.1
  631.  
  632. [MWingUL]
  633. PositionX=-0.540
  634. PositionY=0.601
  635. PositionZ=-0.211
  636. Value=1.0
  637.  
  638. [MWingUR]
  639. PositionX=0.540
  640. PositionY=0.601
  641. PositionZ=-0.211
  642. Value=1.0
  643.  
  644. [MWingLL]
  645. PositionX=-0.540
  646. PositionY=0.259
  647. PositionZ=-0.292
  648. Value=1.0
  649.  
  650. [MWingLR]
  651. PositionX=0.540
  652. PositionY=0.259
  653. PositionZ=-0.292
  654. Value=1.0
  655.  
  656. [Engine]
  657. PositionX=0.0
  658. PositionY=0.3544
  659. PositionZ=0.177
  660. Value=QMasEcn
  661.  
  662. [Tank]
  663. PositionX=0.0
  664. PositionY=0.3544
  665. PositionZ=-0.107
  666. Value=QMasTnk
  667.  
  668. [BodyN]
  669. PositionX=0.0
  670. PositionY=0.449
  671. PositionZ=-0.200
  672. Value=1.8
  673.  
  674. [BodyS]
  675. PositionX=0.0
  676. PositionY=0.449
  677. PositionZ=-0.500
  678. Value=1.8
  679.  
  680. [Tail]
  681. PositionX=0.0
  682. PositionY=0.3544
  683. PositionZ=-1.29
  684. Value=QMasTai
  685.  
  686. [Servos]
  687. PositionX=0.0
  688. PositionY=0.23
  689. PositionZ=-0.05
  690. Value=QMasSrv
  691.  
  692. [BatteryAndRec]
  693. PositionX=0.0
  694. PositionY=0.145
  695. PositionZ=0.07
  696. Value=QMasBat
  697.  
  698. [LGearLeft]
  699. PositionX=-0.080
  700. PositionY=0.040
  701. PositionZ=-0.13
  702. Value=0.080
  703.  
  704. [LGearRight]
  705. PositionX=+0.080
  706. PositionY=0.040
  707. PositionZ=-0.13
  708. Value=0.080
  709.  
  710. ;All forces next:
  711.  
  712. ;Prop simulation with aerosurfaces and winds
  713. [WindForces]
  714. PropN
  715. PropS
  716. ;Wings
  717. WingUL
  718. WingUR
  719. WingLL
  720. WingLR
  721. WingULS
  722. WingURS
  723. WingLLS
  724. WingLRS
  725. ;Tail surfaces
  726. TailFinN
  727. HorFinLN
  728. HorFinRN
  729. TailFinS
  730. HorFinLS
  731. HorFinRS
  732. ;Control Surfaces
  733. ElevL
  734. ElevR
  735. RudderN
  736. AileronLL
  737. AileronLR
  738. AileronUL
  739. AileronUR
  740. ;
  741. BodyDrag
  742.  
  743. [BodyDrag]
  744. PositionX=0.0
  745. PositionY=0.355
  746. PositionZ=-0.221
  747. VectorX=0.0
  748. VectorY=0.0
  749. VectorZ=1.0
  750. UpVectorX=0.0
  751. UpVectorY=1.0
  752. UpVectorZ=0.0
  753. Area=QVBdAre
  754. CoeffOfLift=0.0
  755. ;0.1=reasonably clean; 0.05 super clean; 0.15 dirty
  756. CoeffOfDrag=0.12
  757. OffsetFactor=1.0
  758.  
  759. ;hub at 0, 0.4485, 0.38
  760. [PropN]
  761. PositionX=0.0
  762. ;PositionY=0.713
  763. PositionY=0.4485+((QProDia/2.0)*0.8)
  764. PositionZ=0.380
  765. VectorX=0.99313
  766. VectorY=0.0
  767. VectorZ=0.11702
  768. UpVectorX=-0.11702
  769. UpVectorY=0.0
  770. UpVectorZ=0.99313
  771. ;Area=0.0008
  772. Area=(QProAre/2)*0.3
  773. CoeffOfLift=CLTableProp(_AngleOfAttack)
  774. CoeffOfDrag=CDTableProp(_AngleOfAttack)
  775. OffsetFactor=cos(_AngleOfOffset/1.2)
  776.  
  777. [PropS]
  778. PositionX=0.0
  779. PositionY=0.4485-((QProDia/2.0)*0.8)
  780. PositionZ=0.380
  781. VectorX=-0.99313
  782. VectorY=0.0
  783. VectorZ=0.11702
  784. UpVectorX=0.11702
  785. UpVectorY=0.0
  786. UpVectorZ=0.99313
  787. Area=(QProAre/2)*0.3
  788. CoeffOfLift=CLTableProp(_AngleOfAttack)
  789. CoeffOfDrag=CDTableProp(_AngleOfAttack)
  790. OffsetFactor=cos(_AngleOfOffset/1.2)
  791.  
  792. [WingUL]
  793. PositionX=-0.540
  794. PositionY=0.601
  795. PositionZ=-0.211
  796. VectorX=0.0
  797. VectorY=0.0
  798. VectorZ=1.0
  799. UpVectorX=0.0
  800. UpVectorY=1.0
  801. UpVectorZ=0.0
  802. Area=0.3637
  803. CoeffOfLift=CLTableWing(_AngleOfAttack)
  804. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  805. OffsetFactor=cos(_AngleOfOffset)
  806.  
  807. [WingULS]
  808. PositionX=-0.540
  809. PositionY=0.601
  810. PositionZ=-0.211
  811. VectorX=0.0
  812. VectorY=0.0
  813. VectorZ=-1.0
  814. UpVectorX=0.0
  815. UpVectorY=1.0
  816. UpVectorZ=0.0
  817. Area=0.3637
  818. CoeffOfLift=CLTableWing(_AngleOfAttack)
  819. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  820. OffsetFactor=cos(_AngleOfOffset)
  821.  
  822. [WingUR]
  823. PositionX=0.540
  824. PositionY=0.601
  825. PositionZ=-0.211
  826. VectorX=0.0
  827. VectorY=0.0
  828. VectorZ=1.0
  829. UpVectorX=0.0
  830. UpVectorY=1.0
  831. UpVectorZ=0.0
  832. Area=0.3637
  833. CoeffOfLift=CLTableWing(_AngleOfAttack)
  834. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  835. OffsetFactor=cos(_AngleOfOffset)
  836.  
  837. [WingURS]
  838. PositionX=0.540
  839. PositionY=0.601
  840. PositionZ=-0.211
  841. VectorX=0.0
  842. VectorY=0.0
  843. VectorZ=-1.0
  844. UpVectorX=0.0
  845. UpVectorY=1.0
  846. UpVectorZ=0.0
  847. Area=0.3637
  848. CoeffOfLift=CLTableWing(_AngleOfAttack)
  849. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  850. OffsetFactor=cos(_AngleOfOffset)
  851.  
  852. [WingLL]
  853. PositionX=-0.540
  854. PositionY=0.259
  855. PositionZ=-0.292
  856. VectorX=0.0
  857. VectorY=0.0
  858. VectorZ=1.0
  859. UpVectorX=0.087156
  860. UpVectorY=0.996195
  861. UpVectorZ=0.0
  862. Area=0.2819
  863. CoeffOfLift=CLTableWing(_AngleOfAttack)
  864. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  865. OffsetFactor=cos(_AngleOfOffset)
  866.  
  867. [WingLLS]
  868. PositionX=-0.540
  869. PositionY=0.259
  870. PositionZ=-0.292
  871. VectorX=0.0
  872. VectorY=0.0
  873. VectorZ=-1.0
  874. UpVectorX=0.087156
  875. UpVectorY=0.996195
  876. UpVectorZ=0.0
  877. Area=0.2819
  878. CoeffOfLift=CLTableWing(_AngleOfAttack)
  879. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  880. OffsetFactor=cos(_AngleOfOffset)
  881.  
  882. [WingLR]
  883. PositionX=0.540
  884. PositionY=0.259
  885. PositionZ=-0.292
  886. VectorX=0.0
  887. VectorY=0.0
  888. VectorZ=1.0
  889. UpVectorX=-.087156
  890. UpVectorY=0.996195
  891. UpVectorZ=0.0
  892. Area=0.2819
  893. CoeffOfLift=CLTableWing(_AngleOfAttack)
  894. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  895. OffsetFactor=cos(_AngleOfOffset)
  896.  
  897. [WingLRS]
  898. PositionX=0.540
  899. PositionY=0.259
  900. PositionZ=-0.292
  901. VectorX=0.0
  902. VectorY=0.0
  903. VectorZ=-1.0
  904. UpVectorX=-.087156
  905. UpVectorY=0.996195
  906. UpVectorZ=0.0
  907. Area=0.2819
  908. CoeffOfLift=CLTableWing(_AngleOfAttack)
  909. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  910. OffsetFactor=cos(_AngleOfOffset)
  911.  
  912. [TailFinN]
  913. PositionX=0.0
  914. PositionY=0.479094
  915. PositionZ=-1.31281
  916. VectorX=0.0
  917. VectorY=0.0
  918. VectorZ=1.0
  919. UpVectorX=1.0
  920. UpVectorY=0.0
  921. UpVectorZ=0.0
  922. Area=0.070
  923. CoeffOfLift=CLTableWing(_AngleOfAttack)
  924. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  925. OffsetFactor=cos(_AngleOfOffset)
  926.  
  927. [TailFinS]
  928. PositionX=0.0
  929. PositionY=0.479094
  930. PositionZ=-1.31281
  931. VectorX=0.0
  932. VectorY=0.0
  933. VectorZ=-1.0
  934. UpVectorX=1.0
  935. UpVectorY=0.0
  936. UpVectorZ=0.0
  937. Area=0.070
  938. CoeffOfLift=CLTableWing(_AngleOfAttack)
  939. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  940. OffsetFactor=cos(_AngleOfOffset)
  941.  
  942. [HorFinLN]
  943. PositionX=-0.213
  944. PositionY=0.414
  945. PositionZ=-1.235
  946. VectorX=0.0
  947. VectorY=0.0
  948. VectorZ=1.0
  949. UpVectorX=0.0
  950. UpVectorY=1.0
  951. UpVectorZ=0.0
  952. Area=0.06855
  953. CoeffOfLift=CLTableWing(_AngleOfAttack)
  954. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  955. OffsetFactor=cos(_AngleOfOffset)
  956.  
  957. [HorFinLS]
  958. PositionX=-0.213
  959. PositionY=0.414
  960. PositionZ=-1.235
  961. VectorX=0.0
  962. VectorY=0.0
  963. VectorZ=-1.0
  964. UpVectorX=0.0
  965. UpVectorY=1.0
  966. UpVectorZ=0.0
  967. Area=0.06855
  968. CoeffOfLift=CLTableWing(_AngleOfAttack)
  969. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  970. OffsetFactor=cos(_AngleOfOffset)
  971.  
  972. [HorFinRN]
  973. PositionX=0.213
  974. PositionY=0.414
  975. PositionZ=-1.235
  976. VectorX=0.0
  977. VectorY=0.0
  978. VectorZ=1.0
  979. UpVectorX=0.0
  980. UpVectorY=1.0
  981. UpVectorZ=0.0
  982. Area=0.06855
  983. CoeffOfLift=CLTableWing(_AngleOfAttack)
  984. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  985. OffsetFactor=cos(_AngleOfOffset)
  986.  
  987. [HorFinRS]
  988. PositionX=0.213
  989. PositionY=0.414
  990. PositionZ=-1.235
  991. VectorX=0.0
  992. VectorY=0.0
  993. VectorZ=-1.0
  994. UpVectorX=0.0
  995. UpVectorY=1.0
  996. UpVectorZ=0.0
  997. Area=0.06855
  998. CoeffOfLift=CLTableWing(_AngleOfAttack)
  999. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1000. OffsetFactor=cos(_AngleOfOffset)
  1001.  
  1002. [ElevL]
  1003. PositionX=-0.213
  1004. PositionY=0.414
  1005. PositionZ=-1.235
  1006. VectorX=0.0
  1007. VectorY=sin((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1008. VectorZ=cos((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1009. UpVectorX=0.0
  1010. UpVectorY=cos((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1011. UpVectorZ=-sin((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1012. Area=QEleAre/2.0
  1013. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1014. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1015. OffsetFactor=cos(_AngleOfOffset/1.2)
  1016.  
  1017. [ElevR]
  1018. PositionX=0.213
  1019. PositionY=0.414
  1020. PositionZ=-1.235
  1021. VectorX=0.0
  1022. VectorY=sin((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1023. VectorZ=cos((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1024. UpVectorX=0.0
  1025. UpVectorY=cos((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1026. UpVectorZ=-sin((((1-_Elevator)-0.5)*(-QMaxEle))+QTrmEle)
  1027. Area=QEleAre/2.0
  1028. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1029. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1030. OffsetFactor=cos(_AngleOfOffset/1.2)
  1031.  
  1032. [RudderN]
  1033. PositionX=0.0
  1034. PositionY=0.479094
  1035. PositionZ=-1.420
  1036. VectorX=sin((((1-_Rudder)-0.5)*(QMaxRud))+QTrmRud)
  1037. VectorY=0.0
  1038. VectorZ=cos((((1-_Rudder)-0.5)*(QMaxRud))+QTrmRud)
  1039. UpVectorX=cos((((1-_Rudder)-0.5)*(QMaxRud))+QTrmRud)
  1040. UpVectorY=0.0
  1041. UpVectorZ=-sin((((1-_Rudder)-0.5)*(QMaxRud))+QTrmRud)
  1042. Area=QRudAre
  1043. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1044. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1045. OffsetFactor=cos(_AngleOfOffset/1.2)
  1046.  
  1047. [AileronLL]
  1048. PositionX=-0.762
  1049. PositionY=0.259
  1050. PositionZ=-0.292
  1051. VectorX=0.0
  1052. VectorY=sin(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1053. VectorZ=cos(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1054. UpVectorX=0.0
  1055. UpVectorY=cos(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1056. UpVectorZ=-sin(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1057. Area=QAilAre/4.0
  1058. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1059. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1060. OffsetFactor=cos(_AngleOfOffset/1.2)
  1061.  
  1062. [AileronLR]
  1063. PositionX=0.762
  1064. PositionY=0.259
  1065. PositionZ=-0.292
  1066. VectorX=0.0
  1067. VectorY=sin(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1068. VectorZ=cos(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1069. UpVectorX=0.0
  1070. UpVectorY=cos(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1071. UpVectorZ=-sin(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1072. Area=QAilAre/4.0
  1073. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1074. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1075. OffsetFactor=cos(_AngleOfOffset/1.2)
  1076.  
  1077. [AileronUL]
  1078. PositionX=-0.762
  1079. PositionY=0.601
  1080. PositionZ=-0.292
  1081. VectorX=0.0
  1082. VectorY=sin(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1083. VectorZ=cos(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1084. UpVectorX=0.0
  1085. UpVectorY=cos(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1086. UpVectorZ=-sin(((_Aileron-0.5)*(-QMaxAil))+QTrmAil)
  1087. Area=QAilAre/4.0
  1088. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1089. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1090. OffsetFactor=cos(_AngleOfOffset/1.2)
  1091.  
  1092. [AileronUR]
  1093. PositionX=0.762
  1094. PositionY=0.601
  1095. PositionZ=-0.292
  1096. VectorX=0.0
  1097. VectorY=sin(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1098. VectorZ=cos(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1099. UpVectorX=0.0
  1100. UpVectorY=cos(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1101. UpVectorZ=-sin(((_Aileron-0.5)*(QMaxAil))-QTrmAil)
  1102. Area=QAilAre/4.0
  1103. CoeffOfLift=CLTableWing(_AngleOfAttack)
  1104. CoeffOfDrag=CDTableWing(_AngleOfAttack)
  1105. OffsetFactor=cos(_AngleOfOffset/1.2)
  1106.  
  1107. [Winds]
  1108. PropWindN
  1109. PropWindS
  1110. PropWash
  1111.  
  1112. [PropWash]
  1113. PositionX=0.0
  1114. PositionY=0.713
  1115. PositionZ=0.370
  1116. OrientationX=0.0
  1117. OrientationY=0.0
  1118. OrientationZ=-1.0
  1119. Radius=0.360
  1120. Length=2.5
  1121. WindVectorX=-20.17*exp((-_VectorX)/1.77)*(1-_Throttle)
  1122. WindVectorY=0.0
  1123. WindVectorZ=0.0
  1124.  
  1125. [PropWindN]
  1126. PositionX=-0.010
  1127. PositionY=0.4485+((QProDia/2.0)*0.8)
  1128. PositionZ=0.380
  1129. OrientationX=1.0
  1130. OrientationY=0.0
  1131. OrientationZ=0.0
  1132. Radius=0.005
  1133. Length=0.020
  1134. WindVectorX=((1-_Throttle))*((QProDia/2.0)*0.8*2.0*3.14*(QEngRPM/60))
  1135. WindVectorY=0.0
  1136. WindVectorZ=0.0
  1137.  
  1138. [PropWindS]
  1139. PositionX=0.010
  1140. PositionY=0.4485-((QProDia/2.0)*0.8)
  1141. PositionZ=0.380
  1142. OrientationX=-1.0
  1143. OrientationY=0.0
  1144. OrientationZ=0.0
  1145. Radius=0.005
  1146. Length=0.020
  1147. ;@1000-7000rpm (27.6 - 193.5  m/sec.)
  1148. ;WindVectorX=((1-_Throttle))*(193.0)
  1149. WindVectorX=((1-_Throttle))*((QProDia/2.0)*0.8*2.0*3.14*(QEngRPM/60))
  1150. WindVectorY=0.0
  1151. WindVectorZ=0.0
  1152.  
  1153. [ContactForces]
  1154. SkidNW
  1155. SkidSW
  1156. SkidSE
  1157. SkidNE
  1158.  
  1159. [SkidNW]
  1160. PositionX=-0.257047
  1161. PositionY=0.0
  1162. PositionZ=0.0
  1163. VectorX=0.0
  1164. VectorY=0.0
  1165. VectorZ=1.0
  1166. CoeffOfFriction=QSKDCOF
  1167. OffsetFactor=QSKDDir
  1168.  
  1169. [SkidSW]
  1170. PositionX=-0.0160439
  1171. PositionY=0.244318
  1172. PositionZ=-1.35079
  1173. VectorX=0.0
  1174. VectorY=0.0
  1175. VectorZ=1.0
  1176. CoeffOfFriction=QSKDCOF
  1177. OffsetFactor=QSKDDir
  1178.  
  1179. [SkidSE]
  1180. PositionX=0.0160439
  1181. PositionY=0.244318
  1182. PositionZ=-1.35079
  1183. VectorX=0.0
  1184. VectorY=0.0
  1185. VectorZ=1.0
  1186. CoeffOfFriction=QSKDCOF
  1187. OffsetFactor=QSKDDir
  1188.  
  1189. [SkidNE]
  1190. PositionX=+0.257047
  1191. PositionY=0.0
  1192. PositionZ=0.0
  1193. VectorX=0.0
  1194. VectorY=0.0
  1195. VectorZ=1.0
  1196. CoeffOfFriction=QSKDCOF
  1197. OffsetFactor=QSKDDir
  1198.  
  1199. [Colliders]
  1200. ColliderPropN
  1201. ColliderPropW
  1202. ColliderPropE
  1203. ColliderPropS
  1204. ColliderWingLeft
  1205. ColliderWingRight
  1206. ColliderTail
  1207.  
  1208. [ColliderTail]
  1209. PositionX=0.0
  1210. PositionY=0.414
  1211. PositionZ=-1.23
  1212. Radius=0.17
  1213. Message=Tail
  1214.  
  1215. [ColliderWingLeft]
  1216. PositionX=-0.907
  1217. PositionY=0.43
  1218. PositionZ=-0.252
  1219. Radius=0.171
  1220. Message=Left Wings
  1221.  
  1222. [ColliderWingRight]
  1223. PositionX=0.907
  1224. PositionY=0.43
  1225. PositionZ=-0.252
  1226. Radius=0.171
  1227. Message=Right Wings
  1228.  
  1229. [ColliderPropN]
  1230. PositionX=0.0
  1231. PositionY=0.794
  1232. PositionZ=0.380
  1233. Radius=0.01
  1234. Message=Propeller Disk
  1235.  
  1236. [ColliderPropS]
  1237. PositionX=0.0
  1238. PositionY=0.104
  1239. PositionZ=0.380
  1240. Radius=0.01
  1241. Message=Propeller Disk
  1242.  
  1243. [ColliderPropW]
  1244. PositionX=-0.345
  1245. PositionY=0.449
  1246. PositionZ=0.380
  1247. Radius=0.01
  1248. Message=Propeller Disk
  1249.  
  1250. [ColliderPropE]
  1251. PositionX=0.345
  1252. PositionY=0.449
  1253. PositionZ=0.380
  1254. Radius=0.01
  1255. Message=Propeller Disk
  1256.  
  1257. [3DObjects]
  1258. MeshBody
  1259. PropDisk
  1260. PropDiskLowSpeed
  1261.  
  1262. [MeshBody]
  1263. Shadow=1
  1264. MeshFile=pitts\pitts27.3df
  1265. ScaleX=.003928
  1266. ScaleY=.003928
  1267. ScaleZ=.003928
  1268. RotationX=0
  1269. RotationY=0
  1270. RotationZ=0
  1271. PositionX=-0.064391
  1272. PositionY=+0.459241
  1273. PositionZ=-0.234652
  1274.  
  1275. [PropDisk]
  1276. Shadow=0
  1277. Condition=(1-_Throttle)>0.3
  1278. MeshFile=prop\prop01.3df
  1279. ScaleX=0.342
  1280. ScaleY=0.342
  1281. ScaleZ=0.342
  1282. RotationX=90.0
  1283. RotationY=RotorYPos/1
  1284. RotationZ=0
  1285. PositionX=0.0
  1286. PositionY=0.4492
  1287. PositionZ=0.320098
  1288.  
  1289. [PropDiskLowSpeed]
  1290. Shadow=1
  1291. Condition=!((1-_Throttle)>0.3)
  1292. MeshFile=prop\pprop.3df
  1293. ScaleX=0.0015
  1294. ScaleY=0.0015
  1295. ScaleZ=-0.0015
  1296. RotationX=0.0
  1297. RotationY=0.0
  1298. RotationZ=SlowRotorYPos*1.5
  1299. PositionX=0.0
  1300. PositionY=0.4492
  1301. PositionZ=0.320098
  1302.  
  1303. [SkipRenderOnLowDetail]
  1304. ;body
  1305. ;L_ELLIPSE06_G_11
  1306. ;rudder
  1307. ;L_ELLIPSE06_G_0
  1308. ;cockpit flair
  1309. L_ELLIPSE06_G_1
  1310. ;canopy
  1311. ;L_ELLIPSE06_G_2
  1312. ;exhausts
  1313. L_ELLIPSE06_G_3
  1314. L_ELLIPSE06_G_4
  1315. ;left gear
  1316. ;L_ELLIPSE06_G_5
  1317. ;right gear
  1318. ;L_ELLIPSE06_G_6
  1319. ;right stab
  1320. ;L_ELLIPSE06_G_7
  1321. ;left stab
  1322. ;L_ELLIPSE06_G_8
  1323. ;engine intake screen
  1324. L_ELLIPSE06_G_12
  1325. ;spinner
  1326. ;L_ELLIPSE06_G_13
  1327. ;lower wing
  1328. ;L_ELLIPSE06_G_14
  1329. ;upper wing
  1330. ;L_ELLIPSE06_G_22
  1331. ;upper wing braces
  1332. L_ELLIPSE06_G_23
  1333. L_ELLIPSE06_G_29
  1334. L_ELLIPSE06_G_30
  1335. L_ELLIPSE06_G_31
  1336. L_ELLIPSE03_G_32
  1337. L_ELLIPSE02_G_33
  1338. L_ELLIPSE01_G_34
  1339. ;wing brace wires
  1340. L_CYLINDER19_G_42
  1341. L_CYLINDER20_G_43
  1342. L_CYLINDER23_G_44
  1343. L_CYLINDER24_G_45
  1344. L_CYLINDER21_G_46
  1345. L_CYLINDER22_G_47
  1346. L_CYLINDER18_G_35
  1347. L_CYLINDER17_G_36
  1348. ;wing connectors
  1349. ;L_ELLIPSE06_G_9
  1350. ;L_ELLIPSE06_G_10
  1351. ;gear braces
  1352. ;L_ELLIPSE06_G_15
  1353. ;L_ELLIPSE06_G_16
  1354. ;L_ELLIPSE06_G_17
  1355. ;L_ELLIPSE06_G_18
  1356. ;tail braces
  1357. L_ELLIPSE06_G_19
  1358. L_ELLIPSE06_G_20
  1359. ;cockpit floor
  1360. L_ELLIPSE06_G_21
  1361. ;cockpit seat
  1362. L_ELLIPSE06_G_24
  1363. ;left wheel pant
  1364. ;L_ELLIPSE06_G_25
  1365. ;left wheel
  1366. ;L_ELLIPSE06_G_26
  1367. ;right wheel pant
  1368. ;L_ELLIPSE06_G_27
  1369. ;right wheel
  1370. ;L_ELLIPSE06_G_28
  1371. ;tail wheel hub
  1372. ;L_CYLINDER10_G_37
  1373. ;tail wheel assy
  1374. ;L_CYLINDER11_G_38
  1375. ;L_BOX05_G_39
  1376. ;L_CYLINDER12_G_40
  1377. ;tail wheel
  1378. ;L_TORUS03_G_41
  1379.  
  1380. [SkipRenderOnHighDetail]
  1381. [SkipRenderOnDistance]
  1382. [SkipRenderOnShadow]
  1383. ;body
  1384. ;L_ELLIPSE06_G_11
  1385. ;rudder
  1386. ;L_ELLIPSE06_G_0
  1387. ;cockpit flair
  1388. L_ELLIPSE06_G_1
  1389. ;canopy
  1390. L_ELLIPSE06_G_2
  1391. ;exhausts
  1392. L_ELLIPSE06_G_3
  1393. L_ELLIPSE06_G_4
  1394. ;left gear
  1395. ;L_ELLIPSE06_G_5
  1396. ;right gear
  1397. ;L_ELLIPSE06_G_6
  1398. ;right stab
  1399. ;L_ELLIPSE06_G_7
  1400. ;left stab
  1401. ;L_ELLIPSE06_G_8
  1402. ;engine intake screen
  1403. L_ELLIPSE06_G_12
  1404. ;spinner
  1405. ;L_ELLIPSE06_G_13
  1406. ;lower wing
  1407. ;L_ELLIPSE06_G_14
  1408. ;upper wing
  1409. ;L_ELLIPSE06_G_22
  1410. ;upper wing braces
  1411. L_ELLIPSE06_G_23
  1412. L_ELLIPSE06_G_29
  1413. L_ELLIPSE06_G_30
  1414. L_ELLIPSE06_G_31
  1415. L_ELLIPSE03_G_32
  1416. L_ELLIPSE02_G_33
  1417. L_ELLIPSE01_G_34
  1418. ;wing brace wires
  1419. L_CYLINDER19_G_42
  1420. L_CYLINDER20_G_43
  1421. L_CYLINDER23_G_44
  1422. L_CYLINDER24_G_45
  1423. L_CYLINDER21_G_46
  1424. L_CYLINDER22_G_47
  1425. L_CYLINDER18_G_35
  1426. L_CYLINDER17_G_36
  1427. ;wing connectors
  1428. L_ELLIPSE06_G_9
  1429. L_ELLIPSE06_G_10
  1430. ;gear braces
  1431. ;L_ELLIPSE06_G_15
  1432. ;L_ELLIPSE06_G_16
  1433. ;L_ELLIPSE06_G_17
  1434. ;L_ELLIPSE06_G_18
  1435. ;tail braces
  1436. L_ELLIPSE06_G_19
  1437. L_ELLIPSE06_G_20
  1438. ;cockpit floor
  1439. L_ELLIPSE06_G_21
  1440. ;cockpit seat
  1441. L_ELLIPSE06_G_24
  1442. ;left wheel pant
  1443. ;L_ELLIPSE06_G_25
  1444. ;left wheel
  1445. L_ELLIPSE06_G_26
  1446. ;right wheel pant
  1447. ;L_ELLIPSE06_G_27
  1448. ;right wheel
  1449. L_ELLIPSE06_G_28
  1450. ;tail wheel hub
  1451. L_CYLINDER10_G_37
  1452. ;tail wheel assy
  1453. L_CYLINDER11_G_38
  1454. L_BOX05_G_39
  1455. L_CYLINDER12_G_40
  1456. ;tail wheel
  1457. L_TORUS03_G_41
  1458.  
  1459. [SkipRenderOnZoom]
  1460. [SkipRenderOnLowFrames]
  1461.  
  1462. [Sounds]
  1463. EngineSound
  1464.  
  1465. [EngineSound]
  1466. SoundFile=sengine.wav
  1467. PositionX=0.06
  1468. PositionY=0.09
  1469. PositionZ=-0.17
  1470. OrientationX=0.0
  1471. OrientationY=0.0
  1472. OrientationZ=-1
  1473. InsideConeAngle=90
  1474. OutsideConeAngle=180
  1475. ConeOutsideVolume=-500
  1476. ;Volume=0.0
  1477. Volume=((1-_Throttle)*QSEnVol)+600
  1478. On=(1-_Throttle)-.1
  1479. Off=0.0
  1480. Frequency=(((1-_Throttle))*(+40000))+100
  1481.  
  1482. [Views]
  1483. FollowCam
  1484. Pilot
  1485. WingCam
  1486.  
  1487. [Pilot]
  1488. Description="CockPit View"
  1489. PositionX=_CGX
  1490. PositionY=_CGY+.31
  1491. PositionZ=_CGZ
  1492. VectorX=0.0    
  1493. VectorY=0.0
  1494. VectorZ=1.0
  1495. UpVectorX=0.0
  1496. UpVectorY=1.0
  1497. UpVectorZ=0.0
  1498.  
  1499. [FollowCam]
  1500. Description="Follow Cam"
  1501. PositionX=_CGX-(_SpeedVectorX*2.5)
  1502. PositionY=_CGY-(_SpeedVectorY*2.5)
  1503. PositionZ=_CGZ-(_SpeedVectorZ*2.5)
  1504. VectorX=_SpeedVectorX
  1505. VectorY=_SpeedVectorY
  1506. VectorZ=_SpeedVectorZ
  1507. UpVectorX=_UpVecX
  1508. UpVectorY=_UpVecY
  1509. UpVectorZ=_UpVecZ
  1510.  
  1511. [WingCam]
  1512. Description="WingCam"
  1513. PositionX=-1.599
  1514. PositionY=0.394
  1515. PositionZ=-0.18
  1516. VectorX=1.0    
  1517. VectorY=0.0
  1518. VectorZ=0.0
  1519. UpVectorX=0.0
  1520. UpVectorY=1.0
  1521. UpVectorZ=0.0
  1522.  
  1523. [Models]
  1524. SmokePuffs
  1525.  
  1526. [SmokePuffs]
  1527. FileName=smoke\smoke.3dm
  1528. Static=0
  1529. NoPhysics=0
  1530.  
  1531. ;;;;;;;;;;;;;;End;;;;;;;;;;;;;;