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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 200,000
Max Cl/Cd: 65.44 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg4-il-200000.txt
Download as CSV file: xf-fg4-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3249   0.10778   0.10441  -0.0210   1.0000   0.0429
  -9.000  -0.3291   0.10568   0.10236  -0.0200   1.0000   0.0433
  -8.750  -0.3349   0.10358   0.10031  -0.0190   1.0000   0.0438
  -8.500  -0.3216   0.09994   0.09668  -0.0233   0.9968   0.0448
  -8.250  -0.3082   0.09592   0.09266  -0.0293   0.9920   0.0460
  -8.000  -0.3093   0.09148   0.08820  -0.0399   0.9831   0.0471
  -7.750  -0.3073   0.08498   0.08154  -0.0524   0.9702   0.0475
  -7.500  -0.2856   0.08213   0.07881  -0.0494   0.9685   0.0481
  -7.250  -0.2614   0.07876   0.07545  -0.0515   0.9652   0.0489
  -7.000  -0.2459   0.07533   0.07200  -0.0538   0.9570   0.0500
  -6.750  -0.2275   0.07127   0.06790  -0.0577   0.9489   0.0512
  -6.500  -0.2018   0.06643   0.06292  -0.0640   0.9429   0.0533
  -6.250  -0.1878   0.06068   0.05676  -0.0692   0.9314   0.0553
  -6.000  -0.1688   0.05765   0.05382  -0.0693   0.9247   0.0560
  -5.750  -0.1436   0.05473   0.05090  -0.0709   0.9194   0.0572
  -5.500  -0.1120   0.05142   0.04748  -0.0740   0.9163   0.0594
  -5.000  -0.0648   0.04453   0.04009  -0.0763   0.9023   0.0652
  -4.750  -0.0435   0.04228   0.03784  -0.0761   0.8940   0.0667
  -4.500  -0.0130   0.04105   0.03593  -0.0762   0.8880   0.0745
  -4.250   0.0224   0.03670   0.03180  -0.0796   0.8860   0.0766
  -4.000   0.0441   0.03495   0.03003  -0.0790   0.8753   0.0796
  -3.750   0.0811   0.03274   0.02738  -0.0807   0.8703   0.0883
  -3.500   0.1045   0.03075   0.02544  -0.0804   0.8585   0.0913
  -3.250   0.1474   0.02888   0.02322  -0.0833   0.8520   0.1032
  -3.000   0.1672   0.02724   0.02161  -0.0819   0.8364   0.1077
  -2.750   0.1843   0.02613   0.02027  -0.0794   0.8203   0.1201
  -2.500   0.2074   0.02497   0.01908  -0.0784   0.8045   0.1288
  -2.250   0.2309   0.02356   0.01756  -0.0776   0.7889   0.1436
  -1.750   0.3119   0.00835   0.00218  -0.0816   0.7315   0.2282
  -1.500   0.3296   0.00725   0.00119  -0.0803   0.7163   0.2549
  -1.250   0.3716   0.01848   0.01087  -0.0787   0.7235   0.1038
  -1.000   0.4097   0.01794   0.00978  -0.0786   0.7058   0.0739
  -0.750   0.4409   0.01667   0.00839  -0.0790   0.6861   0.0698
  -0.500   0.4700   0.01613   0.00765  -0.0787   0.6710   0.0665
  -0.250   0.4961   0.01579   0.00716  -0.0778   0.6554   0.0653
   0.250   0.5406   0.01518   0.00648  -0.0749   0.6264   0.0677
   0.500   0.5589   0.01498   0.00626  -0.0726   0.6120   0.0693
   0.750   0.5784   0.01481   0.00604  -0.0706   0.5993   0.0697
   1.000   0.5956   0.01467   0.00583  -0.0681   0.5849   0.0709
   1.250   0.6116   0.01457   0.00568  -0.0653   0.5710   0.0724
   1.500   0.6260   0.01452   0.00556  -0.0622   0.5568   0.0741
   1.750   0.6414   0.01443   0.00542  -0.0594   0.5437   0.0781
   2.000   0.6570   0.01444   0.00534  -0.0566   0.5300   0.0843
   2.250   0.6723   0.01434   0.00531  -0.0537   0.5167   0.1207
   2.500   0.9122   0.01395   0.00649  -0.1015   0.4567   1.0000
   2.750   0.9266   0.01416   0.00659  -0.0987   0.4383   1.0000
   3.000   0.9373   0.01442   0.00669  -0.0951   0.4135   1.0000
   3.250   0.9492   0.01467   0.00682  -0.0918   0.3942   1.0000
   3.500   0.9602   0.01497   0.00697  -0.0884   0.3728   1.0000
   3.750   0.9726   0.01529   0.00716  -0.0853   0.3530   1.0000
   4.000   0.9856   0.01563   0.00738  -0.0824   0.3352   1.0000
   4.250   0.9992   0.01599   0.00763  -0.0796   0.3185   1.0000
   4.500   1.0132   0.01635   0.00789  -0.0770   0.3048   1.0000
   5.000   1.0437   0.01704   0.00845  -0.0723   0.2781   1.0000
   5.250   1.0587   0.01742   0.00877  -0.0699   0.2646   1.0000
   5.500   1.0733   0.01782   0.00910  -0.0675   0.2508   1.0000
   5.750   1.0876   0.01825   0.00945  -0.0652   0.2376   1.0000
   6.000   1.1018   0.01870   0.00984  -0.0628   0.2242   1.0000
   6.250   1.1176   0.01909   0.01022  -0.0608   0.2130   1.0000
   6.500   1.1290   0.01969   0.01070  -0.0581   0.1938   1.0000
   6.750   1.1421   0.02024   0.01117  -0.0557   0.1787   1.0000
   7.000   1.1526   0.02093   0.01175  -0.0530   0.1562   1.0000
   7.250   1.1603   0.02180   0.01247  -0.0499   0.1308   1.0000
   7.500   1.1648   0.02289   0.01336  -0.0465   0.1034   1.0000
   7.750   1.1729   0.02379   0.01418  -0.0438   0.0910   1.0000
   8.000   1.1821   0.02465   0.01502  -0.0412   0.0856   1.0000
   8.250   1.1931   0.02543   0.01582  -0.0390   0.0835   1.0000
   8.500   1.2033   0.02627   0.01668  -0.0368   0.0818   1.0000
   8.750   1.2127   0.02718   0.01763  -0.0345   0.0803   1.0000
   9.000   1.2230   0.02805   0.01856  -0.0325   0.0798   1.0000
   9.250   1.2320   0.02904   0.01961  -0.0304   0.0791   1.0000
   9.500   1.2399   0.03011   0.02077  -0.0284   0.0783   1.0000
   9.750   1.2475   0.03125   0.02198  -0.0264   0.0778   1.0000
  10.000   1.2529   0.03258   0.02338  -0.0243   0.0770   1.0000
  10.250   1.2590   0.03391   0.02478  -0.0225   0.0767   1.0000
  10.500   1.2645   0.03534   0.02629  -0.0208   0.0766   1.0000
  10.750   1.2683   0.03695   0.02799  -0.0191   0.0763   1.0000
  11.000   1.2731   0.03856   0.02968  -0.0176   0.0762   1.0000
  11.250   1.2766   0.04035   0.03155  -0.0162   0.0760   1.0000
  11.500   1.2789   0.04233   0.03360  -0.0150   0.0756   1.0000
  11.750   1.2814   0.04435   0.03569  -0.0139   0.0753   1.0000
  12.000   1.2842   0.04640   0.03781  -0.0129   0.0750   1.0000
  12.250   1.2867   0.04853   0.04000  -0.0121   0.0746   1.0000
  12.500   1.2893   0.05070   0.04223  -0.0113   0.0742   1.0000
  12.750   1.2895   0.05309   0.04463  -0.0105   0.0731   1.0000
  13.000   1.2929   0.05516   0.04670  -0.0097   0.0723   1.0000
  13.250   1.2988   0.05703   0.04864  -0.0091   0.0720   1.0000
  13.500   1.3049   0.05895   0.05063  -0.0086   0.0717   1.0000
  13.750   1.3111   0.06085   0.05262  -0.0082   0.0714   1.0000
  14.000   1.3174   0.06275   0.05459  -0.0078   0.0710   1.0000
  14.250   1.3236   0.06468   0.05661  -0.0074   0.0707   1.0000
  14.500   1.3294   0.06668   0.05869  -0.0071   0.0702   1.0000
  14.750   1.3351   0.06871   0.06079  -0.0069   0.0697   1.0000
  15.000   1.3392   0.07094   0.06311  -0.0068   0.0689   1.0000
  15.250   1.3461   0.07282   0.06506  -0.0066   0.0686   1.0000
  15.500   1.3510   0.07495   0.06726  -0.0065   0.0679   1.0000
  15.750   1.3584   0.07676   0.06914  -0.0063   0.0677   1.0000
  16.000   1.3633   0.07888   0.07129  -0.0062   0.0666   1.0000
  16.250   1.3708   0.08070   0.07319  -0.0061   0.0665   1.0000
  16.500   1.3825   0.08184   0.07428  -0.0055   0.0653   1.0000
  16.750   1.3948   0.08297   0.07544  -0.0049   0.0647   1.0000
  17.000   1.3976   0.08542   0.07801  -0.0049   0.0639   1.0000
  17.250   1.3975   0.08831   0.08104  -0.0055   0.0637   1.0000
  17.500   1.3937   0.09177   0.08466  -0.0064   0.0633   1.0000
  17.750   1.3887   0.09545   0.08850  -0.0075   0.0627   1.0000
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