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GOE 801 (MVA 301) AIRFOIL (goe801-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 801 (MVA 301) AIRFOIL (goe801-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.04 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe801-il-1000000.txt
Download as CSV file: xf-goe801-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2075   0.09702   0.09525  -0.0498   0.9295   0.0173
  -8.750  -0.2045   0.09364   0.09183  -0.0522   0.9186   0.0173
  -8.500  -0.1955   0.09035   0.08851  -0.0514   0.9112   0.0175
  -8.250  -0.1862   0.08785   0.08599  -0.0517   0.9034   0.0176
  -8.000  -0.1773   0.08541   0.08353  -0.0525   0.8950   0.0177
  -7.750  -0.1682   0.08295   0.08104  -0.0537   0.8872   0.0179
  -7.500  -0.1592   0.08042   0.07849  -0.0553   0.8789   0.0181
  -7.250  -0.1497   0.07783   0.07587  -0.0573   0.8713   0.0184
  -7.000  -0.1360   0.07487   0.07288  -0.0606   0.8637   0.0187
  -6.750  -0.1205   0.07171   0.06968  -0.0644   0.8568   0.0193
  -6.500  -0.0914   0.06555   0.06345  -0.0776   0.8486   0.0205
  -6.250  -0.0672   0.06097   0.05878  -0.0842   0.8419   0.0206
  -6.000  -0.0453   0.05598   0.05373  -0.0898   0.8351   0.0207
  -5.750  -0.0277   0.05331   0.05101  -0.0913   0.8284   0.0209
  -5.500  -0.0065   0.05092   0.04859  -0.0933   0.8210   0.0210
  -5.250   0.0166   0.04847   0.04606  -0.0957   0.8125   0.0212
  -5.000   0.0418   0.04587   0.04340  -0.0985   0.8038   0.0215
  -4.750   0.0685   0.04320   0.04062  -0.1014   0.7954   0.0220
  -4.500   0.1095   0.03820   0.03542  -0.1076   0.7882   0.0241
  -4.250   0.1436   0.03364   0.03061  -0.1112   0.7807   0.0243
  -4.000   0.1701   0.02880   0.02554  -0.1139   0.7735   0.0246
  -3.750   0.1954   0.02715   0.02380  -0.1148   0.7648   0.0248
  -3.500   0.2219   0.02565   0.02220  -0.1156   0.7559   0.0250
  -3.000   0.2768   0.02267   0.01897  -0.1170   0.7365   0.0260
  -2.750   0.3059   0.02076   0.01684  -0.1176   0.7265   0.0272
  -2.500   0.3381   0.01721   0.01265  -0.1180   0.7159   0.0291
  -2.250   0.3655   0.01624   0.01162  -0.1184   0.7031   0.0294
  -2.000   0.3932   0.01548   0.01074  -0.1186   0.6897   0.0299
  -1.750   0.4212   0.01477   0.00989  -0.1188   0.6762   0.0305
  -1.500   0.4496   0.01405   0.00899  -0.1188   0.6622   0.0316
  -1.250   0.4790   0.01435   0.00900  -0.1185   0.6471   0.0335
  -1.000   0.2166   0.02232   0.01835  -0.0778   0.6578   0.0269
  -0.750   0.5348   0.01204   0.00640  -0.1189   0.6167   0.0355
  -0.500   0.5628   0.01168   0.00592  -0.1189   0.6018   0.0368
   0.250   0.5136   0.01258   0.00668  -0.0882   0.5732   0.0335
   0.500   0.6766   0.01004   0.00368  -0.1185   0.5517   0.0340
   0.750   0.7044   0.00959   0.00321  -0.1184   0.5400   0.0326
   1.000   0.7324   0.00937   0.00295  -0.1184   0.5289   0.0325
   1.250   0.7604   0.00928   0.00281  -0.1183   0.5187   0.0328
   1.500   0.7883   0.00915   0.00264  -0.1183   0.5085   0.0328
   1.750   0.8164   0.00906   0.00252  -0.1183   0.4987   0.0330
   2.000   0.8441   0.00905   0.00247  -0.1183   0.4872   0.0334
   2.250   0.8716   0.00903   0.00238  -0.1182   0.4738   0.0342
   2.500   0.8992   0.00903   0.00233  -0.1182   0.4598   0.0353
   2.750   0.9268   0.00908   0.00234  -0.1181   0.4466   0.0364
   3.000   0.9543   0.00915   0.00238  -0.1181   0.4348   0.0380
   3.250   0.9815   0.00925   0.00243  -0.1180   0.4235   0.0401
   3.750   1.0313   0.00784   0.00285  -0.1174   0.4010   1.0000
   4.000   1.0583   0.00803   0.00295  -0.1172   0.3897   1.0000
   4.250   1.0848   0.00824   0.00308  -0.1171   0.3776   1.0000
   4.500   1.1113   0.00845   0.00322  -0.1169   0.3652   1.0000
   4.750   1.1381   0.00864   0.00335  -0.1167   0.3548   1.0000
   5.000   1.1644   0.00885   0.00351  -0.1165   0.3454   1.0000
   5.250   1.1911   0.00903   0.00366  -0.1164   0.3376   1.0000
   5.500   1.2173   0.00924   0.00383  -0.1162   0.3303   1.0000
   5.750   1.2438   0.00942   0.00399  -0.1161   0.3230   1.0000
   6.000   1.2696   0.00965   0.00418  -0.1158   0.3149   1.0000
   6.250   1.2957   0.00985   0.00436  -0.1156   0.3068   1.0000
   6.500   1.3213   0.01008   0.00456  -0.1153   0.2980   1.0000
   6.750   1.3464   0.01034   0.00477  -0.1150   0.2873   1.0000
   7.000   1.3715   0.01060   0.00499  -0.1147   0.2752   1.0000
   7.250   1.3957   0.01092   0.00524  -0.1142   0.2600   1.0000
   7.500   1.4189   0.01132   0.00554  -0.1136   0.2417   1.0000
   7.750   1.4403   0.01184   0.00592  -0.1127   0.2152   1.0000
   8.000   1.4594   0.01253   0.00642  -0.1115   0.1853   1.0000
   8.250   1.4796   0.01310   0.00688  -0.1104   0.1674   1.0000
   8.750   1.5211   0.01406   0.00773  -0.1085   0.1443   1.0000
   9.000   1.5419   0.01450   0.00814  -0.1075   0.1349   1.0000
   9.250   1.5615   0.01500   0.00859  -0.1064   0.1253   1.0000
   9.500   1.5803   0.01551   0.00906  -0.1051   0.1159   1.0000
   9.750   1.5986   0.01600   0.00953  -0.1038   0.1069   1.0000
  10.000   1.6136   0.01659   0.01006  -0.1018   0.0960   1.0000
  10.250   1.6235   0.01742   0.01078  -0.0992   0.0801   1.0000
  10.500   1.6321   0.01837   0.01163  -0.0964   0.0658   1.0000
  10.750   1.6425   0.01925   0.01248  -0.0941   0.0575   1.0000
  11.000   1.6523   0.02020   0.01340  -0.0918   0.0504   1.0000
  11.250   1.6623   0.02118   0.01435  -0.0896   0.0428   1.0000
  11.500   1.6591   0.02309   0.01611  -0.0861   0.0203   1.0000
  11.750   1.6642   0.02453   0.01758  -0.0836   0.0163   1.0000
  12.000   1.6721   0.02582   0.01894  -0.0817   0.0151   1.0000
  12.250   1.6792   0.02722   0.02040  -0.0798   0.0140   1.0000
  12.500   1.6884   0.02849   0.02174  -0.0783   0.0136   1.0000
  12.750   1.6962   0.02992   0.02325  -0.0767   0.0131   1.0000
  13.000   1.7021   0.03154   0.02495  -0.0752   0.0126   1.0000
  13.250   1.7061   0.03339   0.02688  -0.0736   0.0122   1.0000
  13.500   1.7075   0.03555   0.02912  -0.0720   0.0117   1.0000
  13.750   1.7050   0.03816   0.03185  -0.0704   0.0113   1.0000
  14.000   1.7094   0.04017   0.03394  -0.0694   0.0111   1.0000
  14.250   1.7122   0.04242   0.03627  -0.0684   0.0109   1.0000
  14.500   1.7133   0.04492   0.03886  -0.0676   0.0107   1.0000
  14.750   1.7132   0.04765   0.04168  -0.0669   0.0105   1.0000
  15.000   1.7120   0.05060   0.04473  -0.0663   0.0103   1.0000
  15.250   1.7095   0.05383   0.04806  -0.0660   0.0101   1.0000
  15.500   1.7058   0.05731   0.05163  -0.0658   0.0099   1.0000
  15.750   1.7006   0.06105   0.05548  -0.0657   0.0098   1.0000
  16.000   1.6937   0.06514   0.05968  -0.0659   0.0096   1.0000
  16.250   1.6853   0.06954   0.06418  -0.0663   0.0095   1.0000
  16.500   1.6735   0.07447   0.06923  -0.0669   0.0093   1.0000
  16.750   1.6598   0.07979   0.07467  -0.0677   0.0092   1.0000
  17.000   1.6431   0.08569   0.08070  -0.0688   0.0091   1.0000
  17.250   1.6253   0.09183   0.08697  -0.0701   0.0090   1.0000
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