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GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 402 AIRFOIL (goe402-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.24 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe402-il-1000000.txt
Download as CSV file: xf-goe402-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 402 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2910   0.09334   0.09184  -0.0196   1.0000   0.0092
  -7.750  -0.2898   0.09099   0.08952  -0.0197   1.0000   0.0093
  -7.500  -0.2883   0.08821   0.08677  -0.0218   0.9989   0.0094
  -7.250  -0.2664   0.08374   0.08230  -0.0286   0.9909   0.0094
  -7.000  -0.2492   0.07881   0.07737  -0.0329   0.9815   0.0097
  -6.750  -0.2198   0.07479   0.07332  -0.0398   0.9665   0.0099
  -6.500  -0.1627   0.06912   0.06757  -0.0543   0.9421   0.0105
  -6.250  -0.1218   0.06480   0.06282  -0.0641   0.8360   0.0113
  -6.000  -0.1080   0.06207   0.05985  -0.0667   0.7870   0.0124
  -5.750  -0.0890   0.05893   0.05657  -0.0706   0.7650   0.0125
  -5.500  -0.0691   0.05565   0.05317  -0.0738   0.7480   0.0126
  -5.250  -0.0483   0.05238   0.04979  -0.0764   0.7342   0.0126
  -5.000  -0.0261   0.04895   0.04624  -0.0789   0.7227   0.0126
  -4.750  -0.0087   0.04474   0.04195  -0.0809   0.7128   0.0130
  -4.500   0.0126   0.04269   0.03984  -0.0820   0.7039   0.0133
  -4.250   0.0365   0.04050   0.03755  -0.0834   0.6951   0.0140
  -4.000   0.0727   0.03711   0.03397  -0.0862   0.6870   0.0163
  -3.750   0.1002   0.03392   0.03061  -0.0875   0.6786   0.0164
  -3.500   0.1277   0.03071   0.02723  -0.0885   0.6699   0.0165
  -3.250   0.1494   0.02754   0.02391  -0.0895   0.6614   0.0173
  -3.000   0.1748   0.02594   0.02219  -0.0898   0.6518   0.0179
  -2.750   0.2073   0.02420   0.02023  -0.0895   0.6430   0.0211
  -2.250   0.2587   0.01754   0.01297  -0.0895   0.6249   0.0196
  -2.000   0.2863   0.01394   0.00877  -0.0886   0.6161   0.0219
  -1.750   0.3117   0.01596   0.01108  -0.0891   0.6026   0.0251
  -1.500   0.3388   0.01386   0.00860  -0.0884   0.5914   0.0248
  -1.250   0.3663   0.01304   0.00754  -0.0878   0.5789   0.0267
  -1.000   0.3926   0.01212   0.00643  -0.0876   0.5661   0.0299
  -0.750   0.4190   0.01183   0.00604  -0.0874   0.5511   0.0318
  -0.500   0.4460   0.01120   0.00524  -0.0869   0.5385   0.0328
  -0.250   0.4731   0.01080   0.00470  -0.0866   0.5269   0.0345
   0.000   0.4999   0.01011   0.00386  -0.0861   0.5152   0.0339
   0.250   0.5266   0.00963   0.00327  -0.0857   0.5024   0.0335
   0.500   0.5533   0.00933   0.00288  -0.0853   0.4883   0.0340
   0.750   0.5799   0.00913   0.00259  -0.0850   0.4734   0.0348
   1.000   0.6064   0.00897   0.00237  -0.0846   0.4573   0.0356
   1.250   0.6328   0.00891   0.00223  -0.0843   0.4383   0.0362
   1.500   0.6589   0.00893   0.00215  -0.0839   0.4157   0.0365
   1.750   0.6848   0.00896   0.00208  -0.0835   0.3920   0.0368
   2.000   0.7102   0.00882   0.00184  -0.0830   0.3739   0.0377
   2.250   0.7362   0.00878   0.00173  -0.0827   0.3594   0.0394
   2.500   0.7626   0.00882   0.00171  -0.0823   0.3476   0.0414
   2.750   0.7892   0.00887   0.00173  -0.0821   0.3387   0.0438
   3.000   0.8156   0.00896   0.00179  -0.0818   0.3310   0.0461
   3.250   0.8424   0.00901   0.00184  -0.0816   0.3257   0.0480
   3.500   0.8686   0.00895   0.00194  -0.0813   0.3201   0.1740
   3.750   0.9006   0.00758   0.00222  -0.0828   0.3151   1.0000
   4.000   0.9272   0.00769   0.00232  -0.0825   0.3110   1.0000
   4.250   0.9534   0.00783   0.00244  -0.0822   0.3063   1.0000
   4.500   0.9794   0.00800   0.00257  -0.0819   0.3014   1.0000
   4.750   1.0060   0.00810   0.00268  -0.0817   0.2978   1.0000
   5.000   1.0322   0.00823   0.00282  -0.0814   0.2937   1.0000
   5.250   1.0581   0.00840   0.00297  -0.0810   0.2895   1.0000
   5.500   1.0844   0.00853   0.00312  -0.0808   0.2853   1.0000
   5.750   1.1105   0.00867   0.00324  -0.0805   0.2778   1.0000
   6.000   1.1363   0.00884   0.00341  -0.0802   0.2703   1.0000
   6.250   1.1619   0.00903   0.00357  -0.0799   0.2606   1.0000
   6.500   1.1877   0.00919   0.00373  -0.0796   0.2522   1.0000
   6.750   1.2128   0.00942   0.00392  -0.0792   0.2379   1.0000
   7.000   1.2365   0.00978   0.00418  -0.0786   0.2139   1.0000
   7.250   1.2554   0.01065   0.00472  -0.0774   0.1562   1.0000
   7.500   1.2745   0.01148   0.00534  -0.0762   0.1216   1.0000
   7.750   1.2970   0.01195   0.00577  -0.0754   0.1084   1.0000
   8.000   1.3184   0.01252   0.00624  -0.0746   0.0875   1.0000
   8.250   1.3286   0.01422   0.00749  -0.0721   0.0210   1.0000
   8.500   1.3491   0.01484   0.00812  -0.0710   0.0152   1.0000
   8.750   1.3689   0.01550   0.00882  -0.0698   0.0128   1.0000
   9.000   1.3891   0.01608   0.00948  -0.0687   0.0116   1.0000
   9.250   1.4095   0.01661   0.01008  -0.0677   0.0107   1.0000
   9.500   1.4284   0.01724   0.01077  -0.0665   0.0098   1.0000
   9.750   1.4445   0.01807   0.01167  -0.0648   0.0090   1.0000
  10.000   1.4549   0.01929   0.01303  -0.0623   0.0083   1.0000
  10.250   1.4709   0.01997   0.01379  -0.0607   0.0081   1.0000
  10.500   1.4845   0.02076   0.01466  -0.0588   0.0078   1.0000
  10.750   1.4953   0.02153   0.01551  -0.0563   0.0074   1.0000
  11.000   1.5018   0.02240   0.01645  -0.0533   0.0071   1.0000
  11.250   1.5081   0.02332   0.01745  -0.0504   0.0069   1.0000
  11.500   1.5142   0.02431   0.01850  -0.0478   0.0066   1.0000
  11.750   1.5174   0.02555   0.01981  -0.0452   0.0063   1.0000
  12.000   1.5138   0.02738   0.02174  -0.0424   0.0060   1.0000
  12.250   1.5061   0.02983   0.02431  -0.0400   0.0059   1.0000
  12.500   1.4903   0.03349   0.02813  -0.0383   0.0057   1.0000
  12.750   1.4836   0.03667   0.03144  -0.0376   0.0056   1.0000
  13.000   1.4847   0.03923   0.03410  -0.0373   0.0055   1.0000
  13.250   1.4819   0.04231   0.03730  -0.0372   0.0054   1.0000
  13.500   1.4807   0.04533   0.04042  -0.0373   0.0054   1.0000
  13.750   1.4782   0.04861   0.04380  -0.0375   0.0052   1.0000
  14.000   1.4738   0.05222   0.04751  -0.0380   0.0051   1.0000
  14.250   1.4695   0.05591   0.05131  -0.0386   0.0051   1.0000
  14.500   1.4592   0.06045   0.05596  -0.0393   0.0050   1.0000
  14.750   1.4554   0.06432   0.05993  -0.0403   0.0049   1.0000
  15.000   1.4493   0.06857   0.06429  -0.0414   0.0049   1.0000
  15.250   1.4436   0.07293   0.06875  -0.0426   0.0048   1.0000
  15.500   1.4374   0.07750   0.07343  -0.0440   0.0047   1.0000
  15.750   1.4316   0.08210   0.07813  -0.0455   0.0047   1.0000
  16.000   1.4268   0.08669   0.08282  -0.0472   0.0046   1.0000
  16.250   1.4199   0.09161   0.08786  -0.0489   0.0046   1.0000
  16.500   1.4149   0.09647   0.09281  -0.0509   0.0045   1.0000
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