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GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 372 AIRFOIL (goe372-il)
Reynolds number: 100,000
Max Cl/Cd: 62.67 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe372-il-100000.txt
Download as CSV file: xf-goe372-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3461   0.09429   0.08961  -0.0281   1.0000   0.0737
  -7.250  -0.3553   0.09337   0.08883  -0.0288   1.0000   0.0750
  -7.000  -0.3607   0.09280   0.08836  -0.0337   1.0000   0.0759
  -6.750  -0.3594   0.09145   0.08704  -0.0393   1.0000   0.0763
  -6.500  -0.3579   0.08493   0.08062  -0.0301   1.0000   0.0780
  -6.250  -0.3559   0.08204   0.07778  -0.0272   1.0000   0.0799
  -6.000  -0.3562   0.07972   0.07551  -0.0261   1.0000   0.0821
  -5.750  -0.3567   0.07750   0.07333  -0.0260   1.0000   0.0846
  -5.500  -0.3522   0.07545   0.07128  -0.0301   1.0000   0.0886
  -5.250  -0.3383   0.07235   0.06808  -0.0382   1.0000   0.0906
  -5.000  -0.3414   0.06895   0.06478  -0.0327   1.0000   0.0921
  -4.750  -0.3375   0.06639   0.06224  -0.0306   1.0000   0.0947
  -4.500  -0.3037   0.06307   0.05860  -0.0420   1.0000   0.1044
  -4.250  -0.3088   0.06003   0.05576  -0.0357   1.0000   0.1073
  -4.000  -0.2775   0.05668   0.05208  -0.0430   1.0000   0.1186
  -3.750  -0.2725   0.05367   0.04917  -0.0400   1.0000   0.1213
  -3.500  -0.2440   0.05036   0.04561  -0.0447   1.0000   0.1332
  -3.250  -0.2107   0.04690   0.04202  -0.0484   0.9961   0.1479
  -3.000  -0.1746   0.04383   0.03885  -0.0521   0.9903   0.1668
  -2.750  -0.1304   0.04053   0.03528  -0.0578   0.9845   0.1909
  -2.500  -0.0950   0.03814   0.03275  -0.0608   0.9779   0.2211
  -2.250  -0.0177   0.02917   0.02197  -0.0707   0.9758   0.1153
  -2.000   0.0265   0.02636   0.01857  -0.0740   0.9710   0.1119
  -1.750   0.0664   0.02497   0.01650  -0.0762   0.9637   0.1176
  -1.500   0.1078   0.02344   0.01483  -0.0792   0.9575   0.1231
  -1.250   0.1455   0.02237   0.01339  -0.0809   0.9494   0.1299
  -1.000   0.1891   0.02136   0.01218  -0.0839   0.9432   0.1437
  -0.750   0.2238   0.02073   0.01159  -0.0854   0.9337   0.1656
  -0.500   0.2671   0.02009   0.01100  -0.0885   0.9271   0.1942
  -0.250   0.3043   0.01954   0.01054  -0.0903   0.9176   0.2211
   0.000   0.3408   0.01903   0.01016  -0.0919   0.9084   0.2564
   0.250   0.3890   0.01789   0.00969  -0.0958   0.9028   0.3933
   0.500   0.4438   0.01647   0.00922  -0.1007   0.8967   1.0000
   0.750   0.4881   0.01636   0.00894  -0.1036   0.8888   1.0000
   1.000   0.5226   0.01637   0.00886  -0.1046   0.8776   1.0000
   1.250   0.5583   0.01635   0.00877  -0.1058   0.8671   1.0000
   1.500   0.6003   0.01615   0.00855  -0.1079   0.8597   1.0000
   1.750   0.6301   0.01621   0.00859  -0.1079   0.8474   1.0000
   2.000   0.6596   0.01628   0.00867  -0.1078   0.8352   1.0000
   2.250   0.6889   0.01635   0.00875  -0.1076   0.8230   1.0000
   2.500   0.7180   0.01638   0.00884  -0.1073   0.8103   1.0000
   2.750   0.7464   0.01638   0.00887  -0.1067   0.7970   1.0000
   3.000   0.7739   0.01640   0.00893  -0.1059   0.7833   1.0000
   3.250   0.8007   0.01644   0.00903  -0.1050   0.7695   1.0000
   3.500   0.8293   0.01592   0.00849  -0.1032   0.7492   1.0000
   3.750   0.8511   0.01535   0.00793  -0.1001   0.7168   1.0000
   4.000   0.8735   0.01502   0.00760  -0.0976   0.6862   1.0000
   4.250   0.8957   0.01483   0.00741  -0.0953   0.6542   1.0000
   4.500   0.9164   0.01474   0.00732  -0.0928   0.6140   1.0000
   4.750   0.9319   0.01487   0.00707  -0.0890   0.5347   1.0000
   5.000   0.9440   0.01565   0.00732  -0.0853   0.4160   1.0000
   5.250   0.9470   0.01789   0.00816  -0.0813   0.1979   1.0000
   5.500   0.9536   0.02036   0.00958  -0.0783   0.0605   1.0000
   5.750   0.9716   0.02150   0.01081  -0.0762   0.0535   1.0000
   6.000   0.9894   0.02259   0.01209  -0.0742   0.0497   1.0000
   6.250   1.0030   0.02405   0.01366  -0.0719   0.0454   1.0000
   6.500   1.0144   0.02576   0.01544  -0.0692   0.0433   1.0000
   6.750   1.0307   0.02729   0.01703  -0.0670   0.0428   1.0000
   7.000   1.0516   0.02910   0.01889  -0.0655   0.0427   1.0000
   7.250   1.0801   0.03145   0.02122  -0.0651   0.0430   1.0000
   7.500   1.1145   0.03454   0.02435  -0.0654   0.0438   1.0000
   7.750   1.1406   0.03568   0.02581  -0.0640   0.0456   1.0000
   8.000   1.1685   0.03830   0.02897  -0.0625   0.0493   1.0000
   8.250   1.1910   0.04167   0.03278  -0.0610   0.0513   1.0000
   8.500   1.2096   0.04543   0.03693  -0.0593   0.0530   1.0000
   8.750   1.2277   0.04891   0.04110  -0.0565   0.0601   1.0000
   9.000   1.2379   0.05513   0.04817  -0.0530   0.0751   1.0000
   9.500   1.1409   0.06290   0.05799  -0.0395   0.1139   1.0000
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