
   (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

