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GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 287 AIRFOIL (goe287-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.95 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe287-il-1000000.txt
Download as CSV file: xf-goe287-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 287 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2985   0.09963   0.09765  -0.0061   0.7874   0.0128
  -9.000  -0.2944   0.09629   0.09428  -0.0071   0.7786   0.0132
  -8.750  -0.4068   0.10420   0.10225   0.0040   0.8132   0.0123
  -8.500  -0.3998   0.10128   0.09928   0.0026   0.8008   0.0125
  -8.250  -0.3929   0.09824   0.09620   0.0009   0.7897   0.0129
  -8.000  -0.3862   0.09509   0.09301  -0.0009   0.7792   0.0133
  -7.500  -0.3751   0.08673   0.08461  -0.0103   0.7580   0.0149
  -7.250  -0.3625   0.08191   0.07975  -0.0164   0.7476   0.0150
  -7.000  -0.3476   0.07698   0.07476  -0.0220   0.7364   0.0150
  -6.750  -0.3354   0.07010   0.06781  -0.0288   0.7252   0.0152
  -5.500  -0.2171   0.05153   0.04866  -0.0487   0.6518   0.0190
  -5.250  -0.1896   0.04626   0.04320  -0.0527   0.6397   0.0191
  -5.000  -0.1680   0.03995   0.03667  -0.0565   0.6293   0.0197
  -4.750  -0.1441   0.03864   0.03526  -0.0574   0.6175   0.0202
  -4.500  -0.1183   0.03687   0.03336  -0.0586   0.6071   0.0210
  -4.250  -0.0819   0.03409   0.03032  -0.0599   0.5991   0.0242
  -4.000  -0.0527   0.03029   0.02622  -0.0612   0.5922   0.0243
  -3.750  -0.0264   0.02347   0.01894  -0.0634   0.5871   0.0254
  -3.500   0.0005   0.02287   0.01828  -0.0639   0.5806   0.0260
  -3.250   0.0280   0.02209   0.01738  -0.0644   0.5745   0.0271
  -3.000   0.0572   0.02080   0.01592  -0.0647   0.5696   0.0293
  -2.750   0.0878   0.02093   0.01587  -0.0644   0.5648   0.0312
  -2.500   0.1171   0.01940   0.01407  -0.0648   0.5603   0.0313
  -2.250   0.1461   0.01525   0.00951  -0.0658   0.5570   0.0334
  -2.000   0.1748   0.01462   0.00883  -0.0662   0.5527   0.0345
  -1.750   0.2037   0.01405   0.00815  -0.0664   0.5485   0.0359
  -1.500   0.2330   0.01344   0.00741  -0.0666   0.5446   0.0373
  -1.250   0.2637   0.01194   0.00557  -0.0665   0.5416   0.0320
  -1.000   0.2928   0.01135   0.00491  -0.0667   0.5380   0.0319
  -0.750   0.3219   0.01095   0.00444  -0.0668   0.5344   0.0317
  -0.500   0.3508   0.01028   0.00369  -0.0670   0.5304   0.0319
  -0.250   0.3798   0.00970   0.00309  -0.0672   0.5275   0.0323
   0.000   0.4088   0.00933   0.00271  -0.0674   0.5241   0.0326
   0.250   0.4379   0.00907   0.00243  -0.0677   0.5204   0.0329
   0.500   0.4669   0.00890   0.00222  -0.0679   0.5165   0.0333
   0.750   0.4961   0.00873   0.00205  -0.0682   0.5135   0.0343
   1.000   0.5252   0.00859   0.00192  -0.0684   0.5100   0.0353
   1.250   0.5543   0.00850   0.00181  -0.0687   0.5059   0.0366
   1.500   0.5833   0.00847   0.00174  -0.0689   0.5014   0.0383
   1.750   0.6124   0.00840   0.00169  -0.0691   0.4973   0.0398
   2.000   0.6414   0.00837   0.00166  -0.0694   0.4921   0.0416
   2.250   0.6704   0.00836   0.00164  -0.0696   0.4859   0.0508
   2.500   0.6935   0.00630   0.00180  -0.0692   0.4803   1.0000
   2.750   0.7224   0.00638   0.00182  -0.0695   0.4735   1.0000
   3.000   0.7513   0.00644   0.00186  -0.0697   0.4664   1.0000
   3.250   0.7801   0.00654   0.00190  -0.0699   0.4567   1.0000
   3.500   0.8088   0.00663   0.00195  -0.0702   0.4429   1.0000
   3.750   0.8373   0.00681   0.00202  -0.0704   0.4140   1.0000
   4.000   0.8638   0.00752   0.00232  -0.0707   0.3326   1.0000
   4.250   0.8910   0.00801   0.00261  -0.0710   0.2961   1.0000
   5.000   0.9740   0.00888   0.00323  -0.0716   0.2481   1.0000
   5.250   1.0016   0.00912   0.00342  -0.0718   0.2374   1.0000
   5.500   1.0292   0.00937   0.00363  -0.0720   0.2283   1.0000
   5.750   1.0569   0.00956   0.00381  -0.0721   0.2202   1.0000
   6.000   1.0841   0.00983   0.00402  -0.0723   0.2077   1.0000
   6.250   1.1104   0.01026   0.00431  -0.0724   0.1781   1.0000
   6.500   1.1250   0.01272   0.00590  -0.0715   0.0261   1.0000
   6.750   1.1507   0.01313   0.00634  -0.0714   0.0209   1.0000
   7.000   1.1756   0.01366   0.00689  -0.0712   0.0177   1.0000
   7.250   1.2008   0.01409   0.00736  -0.0710   0.0163   1.0000
   7.500   1.2257   0.01452   0.00784  -0.0708   0.0152   1.0000
   7.750   1.2500   0.01501   0.00836  -0.0705   0.0141   1.0000
   8.000   1.2724   0.01574   0.00914  -0.0700   0.0130   1.0000
   8.250   1.2935   0.01658   0.01007  -0.0693   0.0122   1.0000
   8.500   1.3169   0.01705   0.01059  -0.0690   0.0117   1.0000
   8.750   1.3392   0.01762   0.01120  -0.0685   0.0110   1.0000
   9.000   1.3602   0.01828   0.01190  -0.0678   0.0105   1.0000
   9.250   1.3802   0.01900   0.01266  -0.0671   0.0100   1.0000
   9.500   1.3970   0.01997   0.01369  -0.0659   0.0095   1.0000
   9.750   1.4008   0.02193   0.01580  -0.0633   0.0090   1.0000
  10.000   1.4124   0.02301   0.01696  -0.0615   0.0089   1.0000
  10.250   1.4215   0.02399   0.01801  -0.0594   0.0087   1.0000
  10.500   1.4289   0.02522   0.01932  -0.0574   0.0085   1.0000
  10.750   1.4352   0.02673   0.02091  -0.0558   0.0083   1.0000
  11.000   1.4420   0.02837   0.02263  -0.0547   0.0080   1.0000
  11.250   1.4494   0.03010   0.02445  -0.0539   0.0078   1.0000
  11.500   1.4575   0.03186   0.02627  -0.0533   0.0075   1.0000
  11.750   1.4645   0.03377   0.02824  -0.0528   0.0073   1.0000
  12.000   1.4698   0.03590   0.03044  -0.0523   0.0071   1.0000
  12.250   1.4732   0.03829   0.03290  -0.0519   0.0069   1.0000
  12.500   1.4741   0.04097   0.03566  -0.0516   0.0068   1.0000
  12.750   1.4718   0.04404   0.03880  -0.0511   0.0067   1.0000
  13.000   1.4643   0.04762   0.04247  -0.0504   0.0065   1.0000
  13.250   1.4509   0.05153   0.04648  -0.0483   0.0063   1.0000
  13.500   1.4522   0.05426   0.04932  -0.0480   0.0063   1.0000
  13.750   1.4538   0.05704   0.05220  -0.0479   0.0062   1.0000
  14.000   1.4542   0.05993   0.05519  -0.0478   0.0062   1.0000
  14.250   1.4541   0.06294   0.05830  -0.0477   0.0061   1.0000
  14.500   1.4534   0.06607   0.06154  -0.0476   0.0060   1.0000
  14.750   1.4522   0.06936   0.06494  -0.0476   0.0059   1.0000
  15.000   1.4500   0.07278   0.06847  -0.0476   0.0058   1.0000
  15.250   1.4469   0.07637   0.07219  -0.0476   0.0057   1.0000
  15.500   1.4430   0.08020   0.07615  -0.0479   0.0057   1.0000
  15.750   1.4379   0.08427   0.08034  -0.0484   0.0056   1.0000
  16.000   1.4316   0.08861   0.08481  -0.0490   0.0055   1.0000
  16.250   1.4240   0.09327   0.08962  -0.0500   0.0054   1.0000
  16.500   1.4148   0.09834   0.09483  -0.0512   0.0054   1.0000
  16.750   1.4033   0.10387   0.10053  -0.0528   0.0053   1.0000
  17.000   1.3914   0.10974   0.10655  -0.0549   0.0053   1.0000
  17.250   1.3791   0.11589   0.11286  -0.0575   0.0052   1.0000
  17.500   1.3660   0.12242   0.11954  -0.0604   0.0052   1.0000
  17.750   1.3533   0.12909   0.12635  -0.0638   0.0051   1.0000
  18.000   1.3410   0.13594   0.13333  -0.0675   0.0051   1.0000
  18.250   1.3255   0.14374   0.14129  -0.0718   0.0051   1.0000
  18.500   1.3059   0.15290   0.15062  -0.0772   0.0051   1.0000
  18.750   1.2861   0.16260   0.16048  -0.0832   0.0051   1.0000
  19.000   1.2574   0.17530   0.17340  -0.0912   0.0052   1.0000
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