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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.41 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe240-il-1000000-n5.txt
Download as CSV file: xf-goe240-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3181   0.09509   0.09347  -0.0326   0.9728   0.0052
  -8.750  -0.3174   0.09009   0.08847  -0.0351   0.9628   0.0055
  -8.500  -0.3102   0.08751   0.08588  -0.0364   0.9516   0.0056
  -8.250  -0.3029   0.08506   0.08341  -0.0375   0.9363   0.0058
  -8.000  -0.2987   0.08265   0.08087  -0.0380   0.8792   0.0059
  -7.750  -0.2914   0.07994   0.07791  -0.0399   0.8286   0.0061
  -7.500  -0.2789   0.07610   0.07398  -0.0443   0.8124   0.0065
  -7.250  -0.2647   0.07074   0.06855  -0.0508   0.8019   0.0070
  -6.000  -0.1422   0.04382   0.04120  -0.0855   0.7705   0.0107
  -5.500  -0.0773   0.02849   0.02525  -0.0987   0.7611   0.0141
  -5.250  -0.0504   0.02769   0.02439  -0.0993   0.7563   0.0144
  -5.000  -0.0230   0.01523   0.01077  -0.1031   0.7523   0.0182
  -4.750   0.0041   0.01412   0.00941  -0.1033   0.7478   0.0187
  -4.500   0.0317   0.01362   0.00883  -0.1034   0.7438   0.0191
  -4.250   0.0596   0.01341   0.00858  -0.1035   0.7396   0.0194
  -4.000   0.0873   0.01315   0.00825  -0.1036   0.7345   0.0199
  -3.750   0.1151   0.01262   0.00760  -0.1036   0.7292   0.0203
  -3.500   0.1430   0.01205   0.00691  -0.1037   0.7225   0.0208
  -3.250   0.1708   0.01158   0.00629  -0.1037   0.7160   0.0214
  -3.000   0.1989   0.01114   0.00574  -0.1038   0.7093   0.0221
  -2.750   0.2269   0.01069   0.00517  -0.1037   0.7026   0.0226
  -2.500   0.2550   0.01028   0.00465  -0.1038   0.6947   0.0229
  -2.250   0.2829   0.00994   0.00420  -0.1037   0.6852   0.0231
  -2.000   0.3109   0.00964   0.00380  -0.1037   0.6744   0.0233
  -1.750   0.3389   0.00935   0.00344  -0.1037   0.6646   0.0235
  -1.500   0.3668   0.00909   0.00310  -0.1036   0.6535   0.0236
  -1.250   0.3945   0.00891   0.00282  -0.1035   0.6354   0.0238
  -1.000   0.4213   0.00891   0.00265  -0.1033   0.5969   0.0240
  -0.750   0.4477   0.00892   0.00246  -0.1030   0.5555   0.0241
  -0.500   0.4749   0.00884   0.00226  -0.1029   0.5344   0.0241
  -0.250   0.5024   0.00875   0.00210  -0.1028   0.5198   0.0242
   0.000   0.5298   0.00861   0.00188  -0.1027   0.5043   0.0245
   0.250   0.5573   0.00846   0.00163  -0.1027   0.4882   0.0254
   0.500   0.5849   0.00841   0.00153  -0.1026   0.4746   0.0263
   0.750   0.6125   0.00841   0.00149  -0.1026   0.4611   0.0271
   1.000   0.6400   0.00845   0.00147  -0.1025   0.4437   0.0277
   1.250   0.6661   0.00868   0.00150  -0.1023   0.3975   0.0283
   1.500   0.6911   0.00908   0.00161  -0.1019   0.3389   0.0288
   1.750   0.7177   0.00925   0.00168  -0.1017   0.3159   0.0292
   2.000   0.7445   0.00941   0.00175  -0.1016   0.2982   0.0296
   2.250   0.7714   0.00956   0.00183  -0.1014   0.2803   0.0304
   2.500   0.7982   0.00971   0.00191  -0.1013   0.2638   0.0311
   2.750   0.8247   0.00989   0.00202  -0.1011   0.2437   0.0316
   3.000   0.8506   0.01016   0.00216  -0.1009   0.2157   0.0320
   3.250   0.8754   0.01056   0.00238  -0.1005   0.1772   0.0370
   3.750   0.9269   0.01105   0.00281  -0.0999   0.1396   0.0876
   4.000   0.9534   0.01110   0.00302  -0.0999   0.1310   0.1987
   4.500   1.0021   0.01008   0.00353  -0.0990   0.1179   1.0000
   4.750   1.0279   0.01035   0.00373  -0.0987   0.1087   1.0000
   5.000   1.0532   0.01067   0.00396  -0.0984   0.0951   1.0000
   5.250   1.0759   0.01128   0.00437  -0.0977   0.0579   1.0000
   5.500   1.1014   0.01156   0.00463  -0.0974   0.0519   1.0000
   5.750   1.1272   0.01178   0.00487  -0.0971   0.0494   1.0000
   6.000   1.1526   0.01204   0.00513  -0.0968   0.0463   1.0000
   6.250   1.1773   0.01237   0.00545  -0.0964   0.0416   1.0000
   6.500   1.2021   0.01267   0.00573  -0.0960   0.0357   1.0000
   6.750   1.2241   0.01330   0.00623  -0.0951   0.0153   1.0000
   7.000   1.2485   0.01362   0.00658  -0.0947   0.0124   1.0000
   7.250   1.2723   0.01401   0.00700  -0.0941   0.0106   1.0000
   7.500   1.2955   0.01444   0.00746  -0.0934   0.0089   1.0000
   7.750   1.3192   0.01479   0.00785  -0.0929   0.0082   1.0000
   8.000   1.3423   0.01519   0.00828  -0.0922   0.0074   1.0000
   8.250   1.3647   0.01564   0.00875  -0.0915   0.0068   1.0000
   8.500   1.3858   0.01623   0.00938  -0.0905   0.0060   1.0000
   8.750   1.4078   0.01667   0.00986  -0.0897   0.0058   1.0000
   9.000   1.4293   0.01714   0.01039  -0.0889   0.0054   1.0000
   9.250   1.4503   0.01763   0.01091  -0.0880   0.0050   1.0000
   9.500   1.4705   0.01816   0.01147  -0.0869   0.0047   1.0000
   9.750   1.4896   0.01876   0.01212  -0.0857   0.0044   1.0000
  10.000   1.5060   0.01956   0.01299  -0.0842   0.0040   1.0000
  10.250   1.5233   0.02023   0.01372  -0.0827   0.0039   1.0000
  10.500   1.5397   0.02090   0.01447  -0.0811   0.0038   1.0000
  10.750   1.5531   0.02162   0.01526  -0.0790   0.0036   1.0000
  11.000   1.5650   0.02240   0.01611  -0.0768   0.0035   1.0000
  11.250   1.5759   0.02325   0.01704  -0.0745   0.0034   1.0000
  11.500   1.5860   0.02418   0.01804  -0.0722   0.0033   1.0000
  11.750   1.5956   0.02517   0.01911  -0.0700   0.0031   1.0000
  12.000   1.6042   0.02627   0.02029  -0.0679   0.0030   1.0000
  12.250   1.6124   0.02743   0.02154  -0.0659   0.0029   1.0000
  12.500   1.6197   0.02873   0.02291  -0.0640   0.0029   1.0000
  12.750   1.6258   0.03019   0.02445  -0.0622   0.0028   1.0000
  13.000   1.6293   0.03198   0.02634  -0.0604   0.0027   1.0000
  13.250   1.6278   0.03435   0.02883  -0.0587   0.0025   1.0000
  13.500   1.6264   0.03689   0.03149  -0.0573   0.0025   1.0000
  13.750   1.6290   0.03911   0.03381  -0.0564   0.0024   1.0000
  14.000   1.6302   0.04156   0.03637  -0.0555   0.0024   1.0000
  14.250   1.6286   0.04440   0.03933  -0.0548   0.0024   1.0000
  14.500   1.6256   0.04748   0.04253  -0.0543   0.0023   1.0000
  14.750   1.6205   0.05096   0.04614  -0.0541   0.0023   1.0000
  15.000   1.6142   0.05472   0.05003  -0.0541   0.0023   1.0000
  15.250   1.6059   0.05893   0.05436  -0.0544   0.0022   1.0000
  15.500   1.5966   0.06353   0.05909  -0.0551   0.0022   1.0000
  15.750   1.5863   0.06850   0.06420  -0.0562   0.0022   1.0000
  16.000   1.5745   0.07384   0.06967  -0.0576   0.0022   1.0000
  16.250   1.5620   0.07946   0.07542  -0.0592   0.0022   1.0000
  16.500   1.5478   0.08548   0.08157  -0.0611   0.0021   1.0000
  16.750   1.5326   0.09174   0.08796  -0.0632   0.0021   1.0000
  17.000   1.5163   0.09834   0.09469  -0.0655   0.0021   1.0000
  17.250   1.5007   0.10499   0.10146  -0.0680   0.0021   1.0000
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