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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 100,000
Max Cl/Cd: 51.91 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg4-il-100000.txt
Download as CSV file: xf-fg4-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 4                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3743   0.10341   0.09905  -0.0194   1.0000   0.0853
  -7.750  -0.3993   0.10254   0.09825  -0.0176   1.0000   0.0856
  -7.500  -0.4263   0.10150   0.09724  -0.0183   1.0000   0.0861
  -7.250  -0.4482   0.10030   0.09599  -0.0188   1.0000   0.0864
  -7.000  -0.4289   0.09470   0.09054  -0.0172   0.9977   0.0875
  -6.750  -0.3988   0.09086   0.08674  -0.0177   0.9924   0.0897
  -6.500  -0.3706   0.08710   0.08295  -0.0225   0.9845   0.0931
  -6.250  -0.3472   0.08398   0.07929  -0.0380   0.9657   0.1006
  -6.000  -0.3285   0.07787   0.07341  -0.0379   0.9591   0.1022
  -5.750  -0.3018   0.07434   0.06995  -0.0388   0.9524   0.1053
  -5.500  -0.2742   0.07096   0.06650  -0.0425   0.9429   0.1110
  -5.250  -0.2528   0.06703   0.06224  -0.0478   0.9305   0.1185
  -5.000  -0.2319   0.06407   0.05941  -0.0475   0.9206   0.1227
  -4.750  -0.1409   0.04737   0.04298  -0.0566   0.8870   0.1432
  -4.500  -0.1790   0.05794   0.05307  -0.0520   0.9025   0.1415
  -4.250  -0.1616   0.05570   0.05055  -0.0527   0.8896   0.1545
  -3.750  -0.1121   0.05052   0.04534  -0.0538   0.8718   0.1777
  -3.500  -0.0948   0.04858   0.04331  -0.0530   0.8605   0.1949
  -3.250  -0.0652   0.04620   0.04090  -0.0538   0.8538   0.2171
  -1.750   0.0462   0.03440   0.02952  -0.0398   0.8017   0.4791
  -1.500   0.1688   0.01690   0.00967  -0.0546   0.7742   0.1681
  -1.250   0.1929   0.02984   0.02165  -0.0527   0.7862   0.1320
  -1.000   0.2297   0.02828   0.01972  -0.0527   0.7775   0.1147
  -0.750   0.2794   0.02619   0.01734  -0.0554   0.7708   0.1046
  -0.500   0.3532   0.02446   0.01531  -0.0625   0.7667   0.0996
  -0.250   0.3814   0.02384   0.01458  -0.0619   0.7540   0.1005
   0.000   0.4414   0.02247   0.01316  -0.0674   0.7450   0.1006
   0.250   0.4968   0.02118   0.01191  -0.0721   0.7342   0.1014
   0.500   0.5314   0.02049   0.01126  -0.0730   0.7206   0.1036
   0.750   0.5720   0.01989   0.01058  -0.0748   0.7050   0.1084
   1.000   0.6157   0.01939   0.00994  -0.0773   0.6862   0.1211
   1.250   0.6580   0.01896   0.00947  -0.0796   0.6663   0.1532
   1.500   0.8634   0.01744   0.00936  -0.1168   0.6287   1.0000
   1.750   0.8819   0.01764   0.00939  -0.1146   0.6109   1.0000
   2.000   0.8990   0.01782   0.00941  -0.1120   0.5923   1.0000
   2.250   0.9159   0.01803   0.00948  -0.1096   0.5749   1.0000
   2.500   0.9324   0.01825   0.00958  -0.1070   0.5579   1.0000
   2.750   0.9499   0.01851   0.00972  -0.1048   0.5426   1.0000
   3.000   0.9667   0.01876   0.00986  -0.1024   0.5268   1.0000
   3.250   0.9843   0.01902   0.01001  -0.1002   0.5121   1.0000
   3.500   1.0014   0.01929   0.01017  -0.0979   0.4971   1.0000
   3.750   1.0148   0.01957   0.01042  -0.0949   0.4816   1.0000
   4.000   1.0288   0.01986   0.01067  -0.0921   0.4663   1.0000
   4.250   1.0413   0.02014   0.01088  -0.0889   0.4500   1.0000
   4.500   1.0552   0.02045   0.01112  -0.0861   0.4354   1.0000
   4.750   1.0694   0.02077   0.01137  -0.0835   0.4217   1.0000
   5.000   1.0832   0.02110   0.01162  -0.0807   0.4083   1.0000
   5.250   1.0963   0.02146   0.01195  -0.0779   0.3949   1.0000
   5.500   1.1082   0.02182   0.01227  -0.0748   0.3816   1.0000
   5.750   1.1196   0.02219   0.01260  -0.0717   0.3694   1.0000
   6.250   1.1426   0.02300   0.01334  -0.0657   0.3463   1.0000
   6.500   1.1518   0.02344   0.01373  -0.0624   0.3333   1.0000
   6.750   1.1640   0.02393   0.01413  -0.0597   0.3238   1.0000
   7.000   1.1763   0.02440   0.01468  -0.0570   0.3136   1.0000
   7.250   1.1882   0.02492   0.01517  -0.0544   0.3045   1.0000
   7.500   1.1986   0.02544   0.01573  -0.0516   0.2939   1.0000
   7.750   1.2079   0.02601   0.01632  -0.0487   0.2824   1.0000
   8.000   1.2162   0.02664   0.01693  -0.0457   0.2714   1.0000
   8.250   1.2253   0.02729   0.01764  -0.0429   0.2601   1.0000
   8.500   1.2342   0.02798   0.01839  -0.0402   0.2490   1.0000
   8.750   1.2401   0.02881   0.01923  -0.0372   0.2354   1.0000
   9.000   1.2453   0.02974   0.02017  -0.0343   0.2219   1.0000
   9.250   1.2486   0.03085   0.02128  -0.0313   0.2043   1.0000
   9.500   1.2489   0.03223   0.02262  -0.0283   0.1840   1.0000
   9.750   1.2474   0.03385   0.02416  -0.0253   0.1660   1.0000
  10.000   1.2424   0.03584   0.02604  -0.0222   0.1482   1.0000
  10.250   1.2407   0.03776   0.02791  -0.0198   0.1386   1.0000
  10.500   1.2395   0.03974   0.02989  -0.0176   0.1316   1.0000
  10.750   1.2376   0.04187   0.03201  -0.0156   0.1266   1.0000
  11.000   1.2362   0.04406   0.03417  -0.0138   0.1238   1.0000
  11.250   1.2391   0.04599   0.03620  -0.0124   0.1210   1.0000
  11.500   1.2417   0.04800   0.03828  -0.0111   0.1184   1.0000
  11.750   1.2449   0.05000   0.04032  -0.0100   0.1164   1.0000
  12.000   1.2496   0.05190   0.04225  -0.0090   0.1150   1.0000
  12.250   1.2561   0.05363   0.04400  -0.0080   0.1139   1.0000
  12.500   1.2647   0.05519   0.04553  -0.0070   0.1126   1.0000
  12.750   1.2768   0.05649   0.04685  -0.0060   0.1115   1.0000
  13.000   1.2897   0.05777   0.04821  -0.0052   0.1109   1.0000
  13.250   1.3025   0.05912   0.04966  -0.0044   0.1101   1.0000
  13.500   1.3155   0.06050   0.05113  -0.0037   0.1095   1.0000
  13.750   1.3280   0.06197   0.05272  -0.0030   0.1090   1.0000
  14.000   1.3394   0.06359   0.05446  -0.0023   0.1085   1.0000
  14.250   1.3464   0.06559   0.05659  -0.0018   0.1076   1.0000
  14.500   1.3523   0.06771   0.05885  -0.0013   0.1068   1.0000
  14.750   1.3572   0.06998   0.06126  -0.0009   0.1061   1.0000
  15.000   1.3596   0.07243   0.06385  -0.0007   0.1051   1.0000
  15.250   1.3622   0.07488   0.06640  -0.0005   0.1041   1.0000
  15.500   1.3730   0.07626   0.06771  -0.0002   0.1020   1.0000
  15.750   1.3845   0.07796   0.06945   0.0001   0.1012   1.0000
  16.000   1.3821   0.08110   0.07274   0.0001   0.1004   1.0000
  16.250   1.3734   0.08503   0.07690  -0.0003   0.1001   1.0000
  16.500   1.3567   0.08998   0.08210  -0.0012   0.0998   1.0000
  16.750   1.3443   0.09473   0.08706  -0.0022   0.0999   1.0000
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