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GOE 801 (MVA 301) AIRFOIL (goe801-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 801 (MVA 301) AIRFOIL (goe801-il)
Reynolds number: 100,000
Max Cl/Cd: 55.9 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe801-il-100000.txt
Download as CSV file: xf-goe801-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 801 (MVA 301) 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  -0.3201   0.10824   0.10393  -0.0185   1.0000   0.0651
  -7.250  -0.3395   0.10816   0.10394  -0.0158   1.0000   0.0655
  -7.000  -0.3551   0.10795   0.10381  -0.0158   1.0000   0.0661
  -6.750  -0.3585   0.10747   0.10336  -0.0226   0.9984   0.0667
  -6.500  -0.3371   0.10135   0.09725  -0.0256   0.9939   0.0677
  -6.250  -0.3194   0.09674   0.09265  -0.0231   0.9901   0.0697
  -6.000  -0.2918   0.09275   0.08863  -0.0280   0.9841   0.0731
  -5.750  -0.2601   0.08911   0.08493  -0.0381   0.9747   0.0778
  -5.500  -0.2179   0.08470   0.08037  -0.0544   0.9648   0.0806
  -5.250  -0.2014   0.08038   0.07611  -0.0524   0.9594   0.0824
  -5.000  -0.1725   0.07679   0.07249  -0.0560   0.9534   0.0861
  -4.750  -0.1098   0.07376   0.06907  -0.0758   0.9424   0.0947
  -4.500  -0.0985   0.06906   0.06454  -0.0730   0.9362   0.0967
  -4.250  -0.0743   0.06607   0.06156  -0.0741   0.9284   0.1017
  -3.750   0.0004   0.05927   0.05454  -0.0861   0.9126   0.1160
  -3.500   0.0570   0.05550   0.05052  -0.0961   0.9083   0.1289
  -3.250   0.0765   0.05329   0.04833  -0.0959   0.8971   0.1351
  -3.000   0.1276   0.04987   0.04476  -0.1029   0.8929   0.1496
  -2.750   0.1585   0.04766   0.04243  -0.1056   0.8821   0.1644
  -2.500   0.2118   0.04514   0.03968  -0.1122   0.8776   0.1946
  -2.250   0.2387   0.04283   0.03738  -0.1130   0.8676   0.2126
  -2.000   0.2803   0.04033   0.03480  -0.1162   0.8618   0.2450
  -1.750   0.3073   0.03841   0.03288  -0.1165   0.8516   0.2778
  -0.750   0.4924   0.02898   0.02139  -0.1278   0.8188   0.1447
  -0.500   0.5326   0.02677   0.01879  -0.1284   0.8122   0.1202
  -0.250   0.5628   0.02578   0.01737  -0.1275   0.8006   0.1083
   0.000   0.5998   0.02413   0.01551  -0.1279   0.7944   0.1035
   0.250   0.6265   0.02336   0.01457  -0.1269   0.7815   0.1003
   0.500   0.6546   0.02264   0.01371  -0.1260   0.7700   0.0988
   0.750   0.6878   0.02167   0.01265  -0.1258   0.7624   0.1017
   1.000   0.7136   0.02122   0.01220  -0.1249   0.7492   0.1049
   1.250   0.7399   0.02077   0.01173  -0.1239   0.7369   0.1070
   1.500   0.7681   0.02031   0.01118  -0.1231   0.7260   0.1104
   1.750   0.7983   0.01979   0.01057  -0.1226   0.7154   0.1189
   2.000   0.8252   0.01959   0.01039  -0.1220   0.7021   0.1401
   2.250   0.8508   0.01782   0.01029  -0.1209   0.6901   1.0000
   2.500   0.8788   0.01790   0.01005  -0.1202   0.6783   1.0000
   2.750   0.9078   0.01792   0.00981  -0.1198   0.6670   1.0000
   3.000   0.9332   0.01817   0.00993  -0.1191   0.6534   1.0000
   3.250   0.9591   0.01844   0.01009  -0.1185   0.6405   1.0000
   3.500   0.9856   0.01871   0.01023  -0.1180   0.6282   1.0000
   3.750   1.0132   0.01892   0.01030  -0.1176   0.6169   1.0000
   4.000   1.0394   0.01923   0.01051  -0.1171   0.6047   1.0000
   4.250   1.0642   0.01967   0.01090  -0.1165   0.5925   1.0000
   4.500   1.0901   0.02006   0.01122  -0.1160   0.5812   1.0000
   4.750   1.1182   0.02033   0.01134  -0.1158   0.5706   1.0000
   5.000   1.1419   0.02071   0.01171  -0.1149   0.5572   1.0000
   5.250   1.1658   0.02106   0.01202  -0.1141   0.5437   1.0000
   5.500   1.1901   0.02141   0.01234  -0.1134   0.5310   1.0000
   5.750   1.2164   0.02176   0.01260  -0.1129   0.5203   1.0000
   6.000   1.2405   0.02220   0.01304  -0.1123   0.5092   1.0000
   6.250   1.2636   0.02271   0.01362  -0.1115   0.4985   1.0000
   6.500   1.2901   0.02310   0.01392  -0.1112   0.4889   1.0000
   6.750   1.3123   0.02359   0.01449  -0.1103   0.4779   1.0000
   7.000   1.3351   0.02409   0.01505  -0.1095   0.4674   1.0000
   7.250   1.3618   0.02444   0.01532  -0.1092   0.4578   1.0000
   7.500   1.3817   0.02499   0.01602  -0.1080   0.4465   1.0000
   7.750   1.4038   0.02550   0.01659  -0.1071   0.4358   1.0000
   8.000   1.4282   0.02584   0.01691  -0.1064   0.4248   1.0000
   8.250   1.4492   0.02621   0.01730  -0.1052   0.4120   1.0000
   8.500   1.4676   0.02664   0.01782  -0.1037   0.3983   1.0000
   8.750   1.4859   0.02707   0.01830  -0.1022   0.3842   1.0000
   9.000   1.5034   0.02749   0.01877  -0.1005   0.3694   1.0000
   9.250   1.5197   0.02796   0.01925  -0.0987   0.3541   1.0000
   9.500   1.5350   0.02854   0.01985  -0.0967   0.3390   1.0000
   9.750   1.5495   0.02922   0.02056  -0.0948   0.3242   1.0000
  10.000   1.5629   0.02998   0.02134  -0.0927   0.3095   1.0000
  10.250   1.5752   0.03080   0.02220  -0.0905   0.2954   1.0000
  10.500   1.5862   0.03164   0.02304  -0.0881   0.2819   1.0000
  10.750   1.5956   0.03248   0.02385  -0.0856   0.2691   1.0000
  11.000   1.5992   0.03338   0.02482  -0.0822   0.2570   1.0000
  11.250   1.6006   0.03446   0.02600  -0.0788   0.2456   1.0000
  11.500   1.6031   0.03561   0.02720  -0.0757   0.2349   1.0000
  11.750   1.6070   0.03678   0.02832  -0.0731   0.2248   1.0000
  12.000   1.6075   0.03825   0.02991  -0.0703   0.2150   1.0000
  12.250   1.6099   0.03982   0.03154  -0.0679   0.2060   1.0000
  12.500   1.6159   0.04125   0.03287  -0.0660   0.1975   1.0000
  12.750   1.6156   0.04319   0.03504  -0.0638   0.1896   1.0000
  13.000   1.6235   0.04474   0.03650  -0.0622   0.1823   1.0000
  13.250   1.6222   0.04689   0.03887  -0.0603   0.1755   1.0000
  13.500   1.6310   0.04846   0.04032  -0.0589   0.1685   1.0000
  13.750   1.6255   0.05101   0.04316  -0.0571   0.1628   1.0000
  14.000   1.6294   0.05291   0.04506  -0.0558   0.1568   1.0000
  14.250   1.6293   0.05530   0.04762  -0.0545   0.1517   1.0000
  14.500   1.6256   0.05796   0.05047  -0.0534   0.1468   1.0000
  14.750   1.6316   0.05978   0.05225  -0.0524   0.1417   1.0000
  15.000   1.6234   0.06304   0.05577  -0.0515   0.1376   1.0000
  15.250   1.6148   0.06638   0.05933  -0.0510   0.1331   1.0000
  15.500   1.6149   0.06878   0.06173  -0.0504   0.1284   1.0000
  15.750   1.6057   0.07258   0.06577  -0.0503   0.1246   1.0000
  16.000   1.5936   0.07686   0.07030  -0.0507   0.1205   1.0000
  16.250   1.5870   0.08036   0.07382  -0.0511   0.1154   1.0000
  16.500   1.5721   0.08546   0.07915  -0.0523   0.1111   1.0000
  16.750   1.5573   0.09081   0.08472  -0.0538   0.1067   1.0000
  17.000   1.5506   0.09477   0.08863  -0.0550   0.1013   1.0000
  17.250   1.5302   0.10156   0.09576  -0.0575   0.0973   1.0000
  17.500   1.5159   0.10738   0.10170  -0.0599   0.0922   1.0000
  17.750   1.1945   0.19529   0.19013  -0.1067   0.1286   1.0000
  18.000   1.1785   0.20618   0.20100  -0.1137   0.1296   1.0000
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