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GOE 738 AIRFOIL (goe738-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 738 AIRFOIL (goe738-il)
Reynolds number: 50,000
Max Cl/Cd: 23.36 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe738-il-50000-n5.txt
Download as CSV file: xf-goe738-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 738 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5294   0.10237   0.09483  -0.0171   1.0000   0.0935
 -11.250  -0.5475   0.09390   0.08639  -0.0222   1.0000   0.0935
 -11.000  -0.5954   0.08002   0.07248  -0.0323   1.0000   0.0933
 -10.750  -0.6465   0.06969   0.06203  -0.0394   1.0000   0.0929
 -10.500  -0.6866   0.06327   0.05544  -0.0415   1.0000   0.0928
 -10.250  -0.7179   0.05876   0.05071  -0.0404   1.0000   0.0932
 -10.000  -0.7394   0.05463   0.04625  -0.0390   1.0000   0.0940
  -9.750  -0.7392   0.05185   0.04332  -0.0380   1.0000   0.0954
  -9.500  -0.7270   0.05009   0.04156  -0.0375   1.0000   0.0972
  -9.250  -0.7196   0.04794   0.03930  -0.0366   1.0000   0.0989
  -9.000  -0.7142   0.04574   0.03692  -0.0354   1.0000   0.1007
  -8.750  -0.7131   0.04378   0.03474  -0.0333   1.0000   0.1024
  -8.500  -0.6930   0.04092   0.03131  -0.0348   0.9660   0.1060
  -8.250  -0.6583   0.03949   0.02992  -0.0372   0.9474   0.1096
  -8.000  -0.6275   0.03781   0.02802  -0.0389   0.9313   0.1138
  -7.750  -0.6005   0.03596   0.02569  -0.0398   0.9164   0.1189
  -7.500  -0.5711   0.03500   0.02478  -0.0406   0.9027   0.1234
  -7.250  -0.5459   0.03388   0.02344  -0.0406   0.8894   0.1291
  -7.000  -0.5225   0.03288   0.02229  -0.0401   0.8762   0.1350
  -6.750  -0.4994   0.03213   0.02146  -0.0395   0.8641   0.1416
  -6.500  -0.4756   0.03126   0.02041  -0.0387   0.8534   0.1493
  -6.250  -0.4535   0.03060   0.01974  -0.0379   0.8417   0.1577
  -6.000  -0.4304   0.02990   0.01896  -0.0371   0.8313   0.1674
  -5.750  -0.4075   0.02928   0.01821  -0.0361   0.8213   0.1799
  -5.500  -0.3851   0.02869   0.01769  -0.0353   0.8113   0.1925
  -5.250  -0.3627   0.02814   0.01713  -0.0342   0.8023   0.2078
  -5.000  -0.3404   0.02763   0.01666  -0.0334   0.7923   0.2252
  -4.750  -0.3181   0.02716   0.01617  -0.0324   0.7842   0.2452
  -4.500  -0.2958   0.02676   0.01579  -0.0316   0.7745   0.2671
  -4.250  -0.2741   0.02632   0.01544  -0.0304   0.7667   0.2905
  -4.000  -0.2526   0.02595   0.01518  -0.0295   0.7576   0.3176
  -3.750  -0.2317   0.02555   0.01493  -0.0282   0.7499   0.3504
  -3.500  -0.2116   0.02519   0.01478  -0.0269   0.7417   0.3908
  -3.250  -0.1918   0.02483   0.01469  -0.0254   0.7336   0.4391
  -3.000  -0.1715   0.02453   0.01465  -0.0235   0.7270   0.4948
  -2.750  -0.1502   0.02443   0.01482  -0.0220   0.7183   0.5539
  -2.500  -0.1261   0.02435   0.01490  -0.0202   0.7120   0.6138
  -2.250  -0.1000   0.02451   0.01520  -0.0192   0.7040   0.6674
  -2.000  -0.0727   0.02469   0.01541  -0.0181   0.6968   0.7154
  -1.750  -0.0405   0.02485   0.01551  -0.0174   0.6915   0.7567
  -1.500  -0.0095   0.02528   0.01594  -0.0176   0.6825   0.7927
  -1.250   0.0275   0.02556   0.01611  -0.0181   0.6762   0.8248
  -1.000   0.0684   0.02594   0.01640  -0.0195   0.6697   0.8530
  -0.750   0.1132   0.02638   0.01675  -0.0220   0.6617   0.8792
  -0.500   0.1585   0.02661   0.01681  -0.0241   0.6561   0.9038
  -0.250   0.2098   0.02701   0.01714  -0.0284   0.6480   0.9244
   0.000   0.2582   0.02715   0.01717  -0.0321   0.6409   0.9437
   0.250   0.3046   0.02710   0.01698  -0.0353   0.6353   0.9615
   0.500   0.3491   0.02738   0.01724  -0.0395   0.6261   0.9780
   0.750   0.3938   0.02719   0.01694  -0.0428   0.6199   0.9918
   1.000   0.4277   0.02736   0.01709  -0.0451   0.6113   1.0000
   1.250   0.4439   0.02745   0.01712  -0.0436   0.6039   1.0000
   1.500   0.4599   0.02754   0.01714  -0.0420   0.5962   1.0000
   1.750   0.4753   0.02772   0.01728  -0.0404   0.5868   1.0000
   2.000   0.4923   0.02768   0.01715  -0.0385   0.5793   1.0000
   2.250   0.5071   0.02798   0.01744  -0.0369   0.5693   1.0000
   2.500   0.5262   0.02781   0.01716  -0.0349   0.5633   1.0000
   2.750   0.5392   0.02844   0.01783  -0.0334   0.5526   1.0000
   3.000   0.5592   0.02832   0.01761  -0.0316   0.5468   1.0000
   3.250   0.5717   0.02904   0.01838  -0.0300   0.5365   1.0000
   3.500   0.5918   0.02902   0.01829  -0.0283   0.5301   1.0000
   3.750   0.6050   0.02970   0.01900  -0.0267   0.5206   1.0000
   4.000   0.6245   0.02980   0.01905  -0.0250   0.5134   1.0000
   4.250   0.6392   0.03036   0.01964  -0.0233   0.5045   1.0000
   4.500   0.6575   0.03064   0.01990  -0.0217   0.4966   1.0000
   4.750   0.6744   0.03106   0.02032  -0.0200   0.4885   1.0000
   5.000   0.6905   0.03153   0.02080  -0.0183   0.4795   1.0000
   5.250   0.7092   0.03181   0.02108  -0.0167   0.4717   1.0000
   5.500   0.7237   0.03242   0.02171  -0.0150   0.4620   1.0000
   5.750   0.7427   0.03272   0.02200  -0.0134   0.4541   1.0000
   6.000   0.7555   0.03349   0.02282  -0.0116   0.4446   1.0000
   6.250   0.7763   0.03372   0.02303  -0.0102   0.4374   1.0000
   6.500   0.7856   0.03472   0.02409  -0.0082   0.4272   1.0000
   6.750   0.8071   0.03491   0.02427  -0.0069   0.4200   1.0000
   7.000   0.8134   0.03612   0.02555  -0.0048   0.4099   1.0000
   7.250   0.8392   0.03608   0.02547  -0.0037   0.4037   1.0000
   7.500   0.8362   0.03798   0.02746  -0.0012   0.3933   1.0000
   7.750   0.8712   0.03730   0.02676  -0.0006   0.3880   1.0000
   8.000   0.8551   0.03999   0.02955   0.0024   0.3766   1.0000
   8.250   0.8909   0.03912   0.02863   0.0032   0.3704   1.0000
   8.500   0.8701   0.04201   0.03161   0.0064   0.3596   1.0000
   8.750   0.8949   0.04177   0.03136   0.0077   0.3522   1.0000
   9.000   0.8772   0.04453   0.03417   0.0103   0.3426   1.0000
   9.250   0.8944   0.04491   0.03455   0.0116   0.3354   1.0000
   9.500   0.8814   0.04794   0.03764   0.0130   0.3261   1.0000
   9.750   0.9018   0.04814   0.03785   0.0142   0.3197   1.0000
  10.000   0.8816   0.05234   0.04213   0.0147   0.3100   1.0000
  10.250   0.9259   0.05009   0.03988   0.0164   0.3051   1.0000
  10.500   0.8807   0.05731   0.04720   0.0158   0.2938   1.0000
  10.750   0.9314   0.05393   0.04380   0.0180   0.2888   1.0000
  11.000   0.8861   0.06168   0.05166   0.0167   0.2772   1.0000
  11.250   0.8812   0.06488   0.05490   0.0166   0.2681   1.0000
  11.500   0.9089   0.06358   0.05360   0.0183   0.2598   1.0000
  11.750   0.8781   0.07040   0.06049   0.0166   0.2486   1.0000
  12.000   0.9366   0.06466   0.05470   0.0202   0.2416   1.0000
  12.250   0.8863   0.07446   0.06462   0.0171   0.2299   1.0000
  12.500   0.9404   0.06929   0.05939   0.0205   0.2242   1.0000
  12.750   0.8781   0.08146   0.07170   0.0159   0.2120   1.0000
  13.000   0.9263   0.07692   0.06713   0.0192   0.2075   1.0000
  13.250   0.8597   0.09070   0.08103   0.0135   0.1947   1.0000
  13.500   0.9049   0.08621   0.07655   0.0167   0.1911   1.0000
  13.750   0.8409   0.10073   0.09114   0.0103   0.1784   1.0000
  14.000   0.8803   0.09689   0.08733   0.0132   0.1755   1.0000
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