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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 50,000
Max Cl/Cd: 37.84 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602-il-50000.txt
Download as CSV file: xf-goe602-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3826   0.10191   0.09539  -0.0240   1.0000   0.2582
  -7.750  -0.3683   0.09778   0.09127  -0.0222   1.0000   0.2701
  -7.500  -0.3680   0.09498   0.08856  -0.0205   1.0000   0.2799
  -7.250  -0.4000   0.09540   0.08919  -0.0178   1.0000   0.2879
  -7.000  -0.3917   0.09197   0.08580  -0.0156   1.0000   0.3015
  -6.750  -0.3918   0.08931   0.08321  -0.0130   1.0000   0.3150
  -6.500  -0.3978   0.08723   0.08123  -0.0098   1.0000   0.3294
  -6.250  -0.4058   0.08529   0.07940  -0.0067   1.0000   0.3446
  -6.000  -0.4189   0.08370   0.07792  -0.0037   1.0000   0.3612
  -5.750  -0.4099   0.08048   0.07475  -0.0001   1.0000   0.3835
  -5.500  -0.4194   0.07878   0.07315   0.0033   1.0000   0.4046
  -5.250  -0.4210   0.07627   0.07069   0.0068   1.0000   0.4257
  -5.000  -0.4351   0.07503   0.06955   0.0106   1.0000   0.4515
  -4.000  -0.3486   0.04225   0.03439  -0.0414   1.0000   0.1528
  -3.750  -0.3251   0.03904   0.03068  -0.0420   1.0000   0.1513
  -3.500  -0.2998   0.03614   0.02718  -0.0424   1.0000   0.1492
  -3.250  -0.2739   0.03363   0.02408  -0.0424   1.0000   0.1472
  -3.000  -0.2499   0.03184   0.02190  -0.0420   1.0000   0.1499
  -2.750  -0.2259   0.03050   0.02006  -0.0415   1.0000   0.1564
  -2.500  -0.2031   0.02905   0.01846  -0.0408   1.0000   0.1616
  -2.250  -0.1796   0.02799   0.01716  -0.0401   1.0000   0.1684
  -2.000  -0.1578   0.02708   0.01621  -0.0391   1.0000   0.1802
  -1.750  -0.1353   0.02641   0.01544  -0.0383   1.0000   0.2007
  -1.500  -0.1111   0.02564   0.01487  -0.0378   1.0000   0.2330
  -1.250  -0.0835   0.02155   0.01408  -0.0354   1.0000   1.0000
  -1.000  -0.0628   0.02200   0.01380  -0.0350   1.0000   1.0000
  -0.750  -0.0436   0.02249   0.01386  -0.0345   1.0000   1.0000
  -0.500  -0.0251   0.02304   0.01407  -0.0341   1.0000   1.0000
  -0.250  -0.0070   0.02363   0.01438  -0.0338   1.0000   1.0000
   0.000   0.0108   0.02429   0.01476  -0.0335   1.0000   1.0000
   0.250   0.0281   0.02499   0.01525  -0.0332   1.0000   1.0000
   0.500   0.0691   0.02625   0.01625  -0.0374   0.9893   1.0000
   0.750   0.1188   0.02764   0.01738  -0.0430   0.9737   1.0000
   1.000   0.1666   0.02890   0.01843  -0.0481   0.9581   1.0000
   1.250   0.2101   0.02997   0.01935  -0.0523   0.9422   1.0000
   1.500   0.2483   0.03087   0.02014  -0.0553   0.9256   1.0000
   1.750   0.2862   0.03176   0.02093  -0.0582   0.9093   1.0000
   2.000   0.3235   0.03260   0.02171  -0.0608   0.8932   1.0000
   2.250   0.3606   0.03340   0.02247  -0.0633   0.8772   1.0000
   2.500   0.3975   0.03415   0.02320  -0.0655   0.8613   1.0000
   2.750   0.4341   0.03484   0.02389  -0.0676   0.8458   1.0000
   3.000   0.4709   0.03547   0.02454  -0.0695   0.8303   1.0000
   3.250   0.5080   0.03600   0.02512  -0.0713   0.8151   1.0000
   3.500   0.5452   0.03647   0.02564  -0.0730   0.8000   1.0000
   3.750   0.5747   0.03705   0.02630  -0.0734   0.7841   1.0000
   4.000   0.6011   0.03768   0.02700  -0.0735   0.7674   1.0000
   4.250   0.6311   0.03819   0.02761  -0.0738   0.7515   1.0000
   4.500   0.6629   0.03860   0.02816  -0.0742   0.7358   1.0000
   4.750   0.6958   0.03891   0.02860  -0.0746   0.7203   1.0000
   5.000   0.7298   0.03910   0.02895  -0.0750   0.7051   1.0000
   5.250   0.7651   0.03916   0.02922  -0.0753   0.6901   1.0000
   5.500   0.8028   0.03905   0.02931  -0.0757   0.6749   1.0000
   5.750   0.8422   0.03877   0.02925  -0.0761   0.6595   1.0000
   6.000   0.8823   0.03835   0.02910  -0.0763   0.6438   1.0000
   6.250   0.9331   0.03709   0.02813  -0.0770   0.6273   1.0000
   6.500   0.9569   0.03722   0.02845  -0.0751   0.6058   1.0000
   6.750   1.0170   0.03454   0.02606  -0.0754   0.5806   1.0000
   7.000   1.0604   0.03310   0.02478  -0.0747   0.5538   1.0000
   7.250   1.0847   0.03191   0.02366  -0.0713   0.5178   1.0000
   7.500   1.1135   0.03040   0.02211  -0.0685   0.4800   1.0000
   7.750   1.1269   0.03024   0.02202  -0.0648   0.4471   1.0000
   8.000   1.1380   0.03011   0.02195  -0.0609   0.4131   1.0000
   8.250   1.1391   0.03010   0.02194  -0.0557   0.3731   1.0000
   8.500   1.1337   0.03055   0.02233  -0.0499   0.3273   1.0000
   8.750   1.1205   0.03165   0.02315  -0.0435   0.2688   1.0000
   9.000   1.1010   0.03397   0.02483  -0.0373   0.2025   1.0000
   9.250   1.0872   0.03705   0.02726  -0.0327   0.1558   1.0000
   9.500   1.0842   0.03987   0.02972  -0.0296   0.1293   1.0000
   9.750   1.0946   0.04240   0.03202  -0.0275   0.1127   1.0000
  10.000   1.1333   0.04497   0.03456  -0.0274   0.0989   1.0000
  10.250   1.1840   0.04848   0.03801  -0.0296   0.0875   1.0000
  10.500   1.2042   0.05152   0.04158  -0.0285   0.0837   1.0000
  10.750   1.2250   0.05527   0.04577  -0.0278   0.0817   1.0000
  11.000   1.2337   0.05903   0.04994  -0.0260   0.0807   1.0000
  11.250   1.2328   0.06276   0.05406  -0.0234   0.0805   1.0000
  11.500   1.2241   0.06647   0.05814  -0.0206   0.0806   1.0000
  11.750   1.2094   0.07029   0.06229  -0.0179   0.0810   1.0000
  12.000   1.1900   0.07439   0.06670  -0.0158   0.0814   1.0000
  12.250   1.1670   0.07893   0.07152  -0.0146   0.0821   1.0000
  12.500   1.1420   0.08406   0.07689  -0.0146   0.0830   1.0000
  12.750   1.1152   0.08992   0.08295  -0.0158   0.0839   1.0000
  13.000   1.0880   0.09658   0.08977  -0.0182   0.0849   1.0000
  13.250   1.0623   0.10396   0.09725  -0.0217   0.0859   1.0000
  13.500   1.0412   0.11171   0.10507  -0.0255   0.0870   1.0000
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