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jsbsim.js

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JSBSim flight dynamics model ported to JavaScript

github.com/csbrandt/JSBSim.js

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(C) 2001,2002 Erik Hofman This configuration file is Freeware; you can redistribute it and/or modify it under the terms of the GNU General Public License version 2, as published by the Free Software Foundation. This file is distributed in the hope that it will be useful, but WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU General Public License for more details. F-22 aerodynamic numbers as presented in the scaleless aerodymanic charts provided by Lockheed-Martin. These are numbers in millimemters. ALPHA ClB ClB ClDr ClDh CnB CnB CnDr CnDr CnDh Cm,-Dh Cma,-Dh Cma Cma,Dh Cm,Dh (LEF) (-30) (+10) (LEF) (LEF) (+30) (+10) (-TV) (+TV) -10 -10.40 -7.10 12.10 1.11 -3.10 -5 20.15 0.00 -9.40 -7.10 7.30 0.00 18.80 0.89 -1.60 14.70 6.20 -1.05 -9.45 -16.30 0 18.80 0.00 -7.90 -7.10 7.45 0.00 19.30 0.72 -0.65 15.65 6.70 0.00 -9.10 -16.10 5 12.75 -0.80 -5.80 -7.10 8.30 -0.40 20.65 0.44 0.00 16.06 7.50 0.55 -9.20 -16.40 10 5.35 1.40 -3.05 -7.10 11.95 -1.85 22.70 0.11 0.50 16.10 7.10 0.30 -9.60 -16.80 15 5.20 -2.50 -0.90 -8.55 13.00 1.00 18.90 0.00 1.50 16.80 7.65 1.05 -8.25 -15.50 20 2.95 11.35 1.10 -6.90 11.80 -5.75 14.65 0.00 4.25 16.25 7.35 0.85 -5.25 -12.30 25 9.00 8.20 -0.55 -3.25 9.60 -19.80 11.40 6.79 5.75 17.50 7.95 1.60 -3.15 -9.95 30 18.30 0.00 -2.50 -3.25 15.00 -8.65 9.50 2.56 7.50 18.35 8.85 2.65 -1.05 -7.95 35 4.75 0.00 -2.50 -1.40 7.00 -2.10 7.50 0.00 8.80 17.75 8.55 2.55 -1.02 -7.65 40 -2.30 0.00 6.10 0.00 7.15 17.02 7.35 1.95 -1.25 -7.20 45 -1.25 1.90 3.70 0.00 5.70 16.55 6.90 1.75 -1.20 -6.80 50 -0.40 2.70 0.00 0.00 4.50 14.70 6.60 2.50 -0.70 -6.90 60 0.00 3.95 0.00 0.00 3.95 8.90 0.40 -2.15 -3.80 -10.90 70 0.00 4.90 0.00 0.00 3.05 0.50 -6.25 -8.70 -9.90 -16.75 80 0.00 6.10 0.00 0.00 1.80 MAX 20.15 20.15 10.4 10.4 15 15 22.7 22.7 22.7 18.35 18.35 18.35 18.35 18.35 F-22 aerodynamic factors derived from the measured values above, devided by the maximum value. These are important numbers because they will represent an approximation of the real numbers when multiplied by the right factor. alpha KlB KlB KlDr KlDh KnB,LEF KnB KnDr KnDr KnDh Km(-Dh) Kma,-Dh Kma Kma,Dh Km,Dh (LEF) (-30) (+10) (LEF) (+30) (+10) (-TV) (+TV) -0.1745 -1.0000 -0.6827 0.5330 0.5820 -0.1366 -0.0873 1.0000 1.0000 -0.9038 -0.6827 0.4867 0.4867 0.8282 0.8674 -0.0705 0.8011 0.3379 -0.0572 -0.5150 -0.8883 0.0000 0.9330 0.9330 -0.7596 -0.6827 0.4967 0.4967 0.8502 0.8821 -0.0286 0.8529 0.3651 0.0000 -0.4959 -0.8774 0.0873 0.6328 0.5931 -0.5577 -0.6827 0.5533 0.5267 0.9097 0.9293 0.0000 0.8752 0.4087 0.0300 -0.5014 -0.8937 0.1745 0.2655 0.3350 -0.2933 -0.6827 0.7967 0.6733 1.0000 1.0049 0.0220 0.8774 0.3869 0.0163 -0.5232 -0.9155 0.2618 0.2581 0.1340 -0.0865 -0.8221 0.8667 0.9333 0.8326 0.8326 0.0661 0.9155 0.4169 0.0572 -0.4496 -0.8447 0.3491 0.1464 0.7097 0.1058 -0.6635 0.7867 0.4033 0.6454 0.6454 0.1872 0.8856 0.4005 0.0463 -0.2861 -0.6703 0.4363 0.4467 0.8536 -0.0529 -0.3125 0.6400 -0.6800 0.5022 0.8011 0.2533 0.9537 0.4332 0.0872 -0.1717 -0.5422 0.5236 0.9082 0.9082 -0.2404 -0.3125 1.0000 0.4233 0.4185 0.5312 0.3304 1.0000 0.4823 0.1444 -0.0572 -0.4332 0.6109 0.2357 0.2357 -0.2404 -0.1346 0.4667 0.3267 0.3304 0.3304 0.3877 0.9673 0.4659 0.1390 -0.0556 -0.4169 0.6981 -0.2212 0.0000 0.2687 0.2687 0.3150 0.9275 0.4005 0.1063 -0.0681 -0.3924 0.7854 -0.1202 0.1827 0.1630 0.1630 0.2511 0.9019 0.3760 0.0954 -0.0654 -0.3706 0.8727 -0.0385 0.2596 0.0000 0.0000 0.1982 0.8011 0.3597 0.1362 -0.0381 -0.3760 1.0472 0.0000 0.3798 0.0000 0.0000 0.1740 0.4850 0.0218 -0.1172 -0.2071 -0.5940 1.2217 0.0000 0.4712 0.0000 0.0000 0.1344 0.0272 -0.3406 -0.4741 -0.5395 -0.9128 1.3963 0.0000 0.5865 0.0000 0.0000 0.0793 F-22 aerodynamic coefficients after being corrected by the estimated multiplication factor. These values are useable to reconstruct the flight characteristics of the aircraft. alpha ClB ClB ClDr ClBdh CnB CnB CnDr CnDr CnBdh CmDh CmDh CmDh CmDh CmDh (LEF) (LEF) (LEF) (-25,-20) (-25,0) (0,0) (+30,0) (+30,20) -0.1745 0.0078 -0.0010 -0.0082 -0.0087 0.2905 -0.0873 0.0189 0.0189 0.0070 -0.0010 -0.0016 -0.0016 -0.0128 -0.0129 0.1499 0.7639 0.3222 -0.0546 -0.4911 -0.8470 0.0000 0.0176 0.0176 0.0059 -0.0010 -0.0016 -0.0016 -0.0131 -0.0131 0.0609 0.8132 0.3482 0.0000 -0.4729 -0.8366 0.0873 0.0119 0.0112 0.0043 -0.0010 -0.0018 -0.0017 -0.0140 -0.0138 0.0000 0.8345 0.3897 0.0286 -0.4781 -0.8522 0.1745 0.0050 0.0063 0.0023 -0.0010 -0.0026 -0.0022 -0.0154 -0.0149 -0.0469 0.8366 0.3689 0.0156 -0.4988 -0.8730 0.2618 0.0049 0.0025 0.0007 -0.0013 -0.0028 -0.0031 -0.0128 -0.0124 -0.1406 0.8730 0.3975 0.0546 -0.4287 -0.8054 0.3491 0.0028 0.0134 -0.0008 -0.0010 -0.0026 -0.0013 -0.0100 -0.0096 -0.3983 0.8444 0.3819 0.0442 -0.2728 -0.6392 0.4363 0.0084 0.0161 0.0004 -0.0005 -0.0021 0.0022 -0.0077 -0.0119 -0.5388 0.9094 0.4131 0.0831 -0.1637 -0.5170 0.5236 0.0171 0.0171 0.0019 -0.0005 -0.0033 -0.0014 -0.0065 -0.0079 -0.7028 0.9535 0.4599 0.1377 -0.0546 -0.4131 0.6109 0.0044 0.0044 0.0019 -0.0002 -0.0015 -0.0011 -0.0051 -0.0049 -0.8247 0.9224 0.4443 0.1325 -0.0530 -0.3975 0.6981 0.0017 0.0000 -0.0041 -0.0040 -0.6700 0.8844 0.3819 0.1013 -0.0650 -0.3741 0.7854 0.0009 0.0003 -0.0025 -0.0024 -0.5342 0.8600 0.3585 0.0909 -0.0624 -0.3534 0.8727 0.0003 0.0004 0.0000 0.0000 -0.4217 0.7639 0.3430 0.1299 -0.0364 -0.3585 1.0472 0.0000 0.0006 0.0000 0.0000 -0.3702 0.4625 0.0208 -0.1117 -0.1975 -0.5664 1.2217 0.0000 0.0007 0.0000 0.0000 -0.2858 0.0260 0.3248 -0.4521 -0.5144 -0.8704 1.3963 0.0000 0.0009 0.0000 0.0000 -0.1687