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GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 795 AIRFOIL (goe795-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.05 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe795-il-1000000.txt
Download as CSV file: xf-goe795-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 795 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.9435   0.03748   0.03550  -0.0594   1.0000   0.0037
 -11.750  -0.9652   0.03070   0.02827  -0.0575   1.0000   0.0037
 -11.500  -0.9628   0.02796   0.02528  -0.0554   1.0000   0.0037
 -11.250  -0.9553   0.02592   0.02304  -0.0533   1.0000   0.0039
 -11.000  -0.9467   0.02405   0.02095  -0.0512   1.0000   0.0040
 -10.750  -0.9350   0.02263   0.01935  -0.0491   1.0000   0.0041
 -10.500  -0.9177   0.02199   0.01869  -0.0476   1.0000   0.0045
 -10.250  -0.8983   0.02171   0.01841  -0.0463   1.0000   0.0048
 -10.000  -0.8734   0.02230   0.01912  -0.0456   1.0000   0.0052
  -9.750  -0.8463   0.02328   0.02025  -0.0450   1.0000   0.0060
  -9.500  -0.8187   0.02439   0.02148  -0.0445   1.0000   0.0067
  -9.000  -0.7676   0.02212   0.01893  -0.0459   0.9978   0.0079
  -8.750  -0.7307   0.02370   0.02073  -0.0473   0.9970   0.0086
  -8.500  -0.6933   0.02551   0.02273  -0.0487   0.9963   0.0094
  -8.250  -0.6604   0.02557   0.02277  -0.0502   0.9951   0.0102
  -8.000  -0.6343   0.02308   0.01997  -0.0516   0.9934   0.0105
  -7.750  -0.6034   0.02325   0.02013  -0.0524   0.9916   0.0111
  -7.500  -0.5751   0.02229   0.01898  -0.0533   0.9892   0.0120
  -7.250  -0.5517   0.01923   0.01550  -0.0539   0.9863   0.0121
  -7.000  -0.5255   0.01674   0.01263  -0.0546   0.9842   0.0125
  -6.750  -0.4951   0.01543   0.01113  -0.0557   0.9829   0.0133
  -6.500  -0.4668   0.01417   0.00967  -0.0561   0.9807   0.0132
  -6.250  -0.4411   0.01335   0.00874  -0.0559   0.9767   0.0136
  -6.000  -0.4102   0.01291   0.00824  -0.0567   0.9742   0.0144
  -5.750  -0.3771   0.01276   0.00809  -0.0580   0.9724   0.0156
  -5.500  -0.3451   0.01189   0.00710  -0.0590   0.9708   0.0159
  -5.250  -0.3133   0.01084   0.00589  -0.0599   0.9694   0.0157
  -5.000  -0.2886   0.01009   0.00503  -0.0592   0.9639   0.0155
  -4.750  -0.2580   0.00946   0.00429  -0.0597   0.9605   0.0155
  -4.500  -0.2244   0.00890   0.00365  -0.0609   0.9580   0.0156
  -4.250  -0.1885   0.00846   0.00312  -0.0627   0.9558   0.0158
  -4.000  -0.1602   0.00813   0.00273  -0.0627   0.9490   0.0162
  -3.750  -0.1252   0.00779   0.00233  -0.0642   0.9445   0.0174
  -3.500  -0.0932   0.00751   0.00203  -0.0650   0.9372   0.0218
  -3.250  -0.0595   0.00728   0.00179  -0.0662   0.9291   0.0300
  -3.000  -0.0309   0.00711   0.00161  -0.0663   0.9179   0.0371
  -2.750  -0.0024   0.00701   0.00146  -0.0663   0.9060   0.0427
  -2.500   0.0249   0.00688   0.00133  -0.0661   0.8923   0.0515
  -2.250   0.0508   0.00669   0.00123  -0.0657   0.8772   0.0846
  -2.000   0.0770   0.00662   0.00115  -0.0652   0.8609   0.1000
  -1.750   0.1024   0.00655   0.00106  -0.0646   0.8432   0.1138
  -1.500   0.1273   0.00647   0.00098  -0.0639   0.8243   0.1329
  -1.250   0.1513   0.00632   0.00093  -0.0630   0.8063   0.1865
  -1.000   0.1755   0.00619   0.00089  -0.0622   0.7907   0.2353
  -0.750   0.2001   0.00609   0.00085  -0.0615   0.7763   0.2744
  -0.500   0.2236   0.00588   0.00083  -0.0606   0.7634   0.3569
  -0.250   0.2455   0.00557   0.00082  -0.0594   0.7496   0.4770
   0.000   0.2653   0.00522   0.00083  -0.0578   0.7329   0.6158
   0.250   0.2797   0.00472   0.00086  -0.0547   0.7189   0.7979
   0.750   0.4117   0.00475   0.00115  -0.0717   0.6844   0.9847
   1.000   0.4504   0.00488   0.00122  -0.0741   0.6684   0.9915
   1.250   0.4895   0.00501   0.00125  -0.0766   0.6460   0.9958
   1.500   0.5331   0.00515   0.00125  -0.0803   0.6131   0.9999
   1.750   0.5557   0.00529   0.00127  -0.0791   0.5817   1.0000
   2.000   0.5761   0.00552   0.00130  -0.0775   0.5325   1.0000
   2.250   0.5960   0.00582   0.00137  -0.0759   0.4769   1.0000
   2.500   0.6158   0.00617   0.00147  -0.0743   0.4186   1.0000
   2.750   0.6364   0.00650   0.00159  -0.0728   0.3708   1.0000
   3.000   0.6583   0.00675   0.00173  -0.0716   0.3385   1.0000
   3.250   0.6803   0.00702   0.00186  -0.0704   0.3081   1.0000
   3.500   0.7023   0.00728   0.00200  -0.0693   0.2781   1.0000
   3.750   0.7236   0.00761   0.00216  -0.0680   0.2354   1.0000
   4.000   0.7422   0.00814   0.00241  -0.0662   0.1733   1.0000
   4.250   0.7631   0.00852   0.00267  -0.0649   0.1425   1.0000
   4.500   0.7841   0.00889   0.00290  -0.0635   0.1106   1.0000
   4.750   0.8033   0.00942   0.00322  -0.0619   0.0680   1.0000
   5.000   0.8251   0.00974   0.00347  -0.0607   0.0558   1.0000
   5.250   0.8477   0.01000   0.00373  -0.0596   0.0507   1.0000
   5.500   0.8701   0.01028   0.00400  -0.0585   0.0476   1.0000
   5.750   0.8916   0.01064   0.00437  -0.0573   0.0423   1.0000
   6.000   0.9146   0.01086   0.00461  -0.0564   0.0402   1.0000
   6.250   0.9382   0.01102   0.00479  -0.0556   0.0388   1.0000
   6.500   0.9614   0.01121   0.00501  -0.0547   0.0352   1.0000
   6.750   0.9836   0.01149   0.00528  -0.0536   0.0292   1.0000
   7.000   1.0002   0.01227   0.00587  -0.0515   0.0083   1.0000
   7.250   1.0201   0.01276   0.00644  -0.0500   0.0065   1.0000
   7.500   1.0378   0.01346   0.00723  -0.0480   0.0052   1.0000
   7.750   1.0565   0.01406   0.00790  -0.0463   0.0049   1.0000
   8.000   1.0762   0.01455   0.00845  -0.0448   0.0048   1.0000
   8.250   1.0943   0.01519   0.00918  -0.0429   0.0045   1.0000
   8.500   1.1125   0.01579   0.00986  -0.0413   0.0043   1.0000
   8.750   1.1300   0.01645   0.01059  -0.0394   0.0041   1.0000
   9.000   1.1485   0.01701   0.01119  -0.0379   0.0037   1.0000
   9.250   1.1638   0.01783   0.01213  -0.0358   0.0036   1.0000
   9.500   1.1797   0.01858   0.01295  -0.0338   0.0034   1.0000
   9.750   1.1914   0.01967   0.01414  -0.0312   0.0031   1.0000
  10.000   1.1936   0.02164   0.01631  -0.0272   0.0029   1.0000
  10.250   1.1922   0.02400   0.01892  -0.0226   0.0028   1.0000
  10.500   1.2001   0.02510   0.02014  -0.0195   0.0027   1.0000
  10.750   1.2072   0.02627   0.02145  -0.0165   0.0027   1.0000
  11.000   1.2124   0.02765   0.02298  -0.0134   0.0026   1.0000
  11.250   1.2142   0.02939   0.02489  -0.0101   0.0026   1.0000
  11.500   1.2131   0.03141   0.02710  -0.0069   0.0026   1.0000
  11.750   1.2096   0.03367   0.02956  -0.0039   0.0026   1.0000
  12.000   1.2027   0.03631   0.03240  -0.0012   0.0026   1.0000
  12.250   1.1948   0.03916   0.03545   0.0010   0.0026   1.0000
  12.500   1.1835   0.04254   0.03902   0.0026   0.0027   1.0000
  12.750   1.1702   0.04646   0.04316   0.0034   0.0026   1.0000
  13.000   1.1467   0.05205   0.04898   0.0031   0.0027   1.0000
  13.250   1.1291   0.05743   0.05455   0.0016   0.0027   1.0000
  13.500   1.1124   0.06321   0.06051  -0.0007   0.0027   1.0000
  13.750   1.0869   0.07090   0.06834  -0.0041   0.0028   1.0000
  14.000   1.0771   0.07660   0.07415  -0.0074   0.0028   1.0000
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