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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 200,000
Max Cl/Cd: 82.49 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe372-il-200000.txt
Download as CSV file: xf-goe372-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 372 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3608   0.08810   0.08497  -0.0343   1.0000   0.0384
  -6.750  -0.3683   0.08345   0.08041  -0.0330   1.0000   0.0389
  -6.500  -0.3719   0.08055   0.07755  -0.0284   1.0000   0.0397
  -6.250  -0.3755   0.07863   0.07568  -0.0255   1.0000   0.0404
  -6.000  -0.3799   0.07687   0.07396  -0.0233   1.0000   0.0412
  -5.750  -0.3653   0.07367   0.07075  -0.0262   0.9977   0.0430
  -5.500  -0.2980   0.06687   0.06371  -0.0488   0.9903   0.0500
  -5.250  -0.2745   0.06039   0.05722  -0.0533   0.9855   0.0519
  -5.000  -0.2460   0.05722   0.05402  -0.0557   0.9816   0.0552
  -4.750  -0.1774   0.05091   0.04716  -0.0728   0.9740   0.0628
  -4.500  -0.1559   0.04523   0.04155  -0.0752   0.9706   0.0651
  -3.750  -0.0378   0.02946   0.02468  -0.0905   0.9567   0.0667
  -3.500  -0.0055   0.02628   0.02112  -0.0924   0.9503   0.0694
  -3.250   0.0326   0.02020   0.01378  -0.0945   0.9463   0.0642
  -3.000   0.0717   0.01931   0.01287  -0.0972   0.9435   0.0699
  -2.750   0.1057   0.01753   0.01064  -0.0982   0.9382   0.0718
  -2.500   0.1418   0.01634   0.00909  -0.0996   0.9333   0.0749
  -2.250   0.1800   0.01505   0.00761  -0.1016   0.9299   0.0791
  -2.000   0.2117   0.01456   0.00709  -0.1023   0.9231   0.0864
  -1.750   0.2464   0.01365   0.00609  -0.1034   0.9178   0.0944
  -1.500   0.2793   0.01302   0.00547  -0.1042   0.9117   0.1088
  -1.250   0.3104   0.01258   0.00505  -0.1047   0.9043   0.1249
  -1.000   0.3409   0.01224   0.00472  -0.1050   0.8967   0.1396
  -0.750   0.3716   0.01198   0.00445  -0.1054   0.8891   0.1583
  -0.500   0.3989   0.01168   0.00424  -0.1051   0.8796   0.1767
  -0.250   0.4281   0.01134   0.00398  -0.1051   0.8714   0.2013
   0.000   0.4546   0.01089   0.00380  -0.1047   0.8616   0.2569
   0.250   0.5010   0.00900   0.00364  -0.1086   0.8537   1.0000
   0.500   0.5283   0.00904   0.00353  -0.1081   0.8433   1.0000
   0.750   0.5553   0.00909   0.00345  -0.1075   0.8325   1.0000
   1.000   0.5809   0.00917   0.00345  -0.1068   0.8201   1.0000
   1.250   0.6065   0.00924   0.00346  -0.1060   0.8070   1.0000
   1.500   0.6321   0.00932   0.00345  -0.1051   0.7931   1.0000
   1.750   0.6575   0.00941   0.00347  -0.1043   0.7788   1.0000
   2.000   0.6830   0.00950   0.00351  -0.1035   0.7644   1.0000
   2.250   0.7084   0.00961   0.00357  -0.1027   0.7499   1.0000
   2.500   0.7339   0.00973   0.00368  -0.1020   0.7354   1.0000
   2.750   0.7583   0.00982   0.00376  -0.1010   0.7173   1.0000
   3.000   0.7798   0.00978   0.00357  -0.0990   0.6818   1.0000
   3.250   0.8020   0.00984   0.00354  -0.0974   0.6463   1.0000
   3.500   0.8249   0.01000   0.00362  -0.0960   0.6132   1.0000
   3.750   0.8464   0.01027   0.00371  -0.0944   0.5707   1.0000
   4.000   0.8631   0.01087   0.00388  -0.0919   0.4935   1.0000
   4.250   0.8785   0.01168   0.00417  -0.0895   0.3794   1.0000
   4.500   0.8833   0.01389   0.00511  -0.0860   0.1583   1.0000
   4.750   0.8955   0.01559   0.00615  -0.0835   0.0390   1.0000
   5.000   0.9168   0.01632   0.00697  -0.0821   0.0332   1.0000
   5.250   0.9380   0.01702   0.00784  -0.0808   0.0294   1.0000
   5.500   0.9583   0.01782   0.00880  -0.0792   0.0280   1.0000
   5.750   0.9765   0.01880   0.00991  -0.0774   0.0272   1.0000
   6.000   0.9932   0.01994   0.01113  -0.0753   0.0270   1.0000
   6.250   1.0095   0.02123   0.01248  -0.0732   0.0271   1.0000
   6.500   1.0272   0.02272   0.01401  -0.0712   0.0278   1.0000
   6.750   1.0490   0.02449   0.01586  -0.0697   0.0290   1.0000
   7.000   1.0737   0.02629   0.01773  -0.0688   0.0290   1.0000
   7.250   1.0999   0.02832   0.01988  -0.0681   0.0288   1.0000
   7.500   1.1351   0.03212   0.02371  -0.0685   0.0332   1.0000
  14.500   0.8087   0.17037   0.16742  -0.0809   0.0503   1.0000
  14.750   0.8118   0.17360   0.17066  -0.0822   0.0472   1.0000
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