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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.21 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe394-il-1000000.txt
Download as CSV file: xf-goe394-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3871   0.11941   0.11763  -0.0044   0.8899   0.0131
  -9.750  -0.3834   0.11617   0.11420  -0.0055   0.8446   0.0132
  -9.500  -0.3777   0.11279   0.11071  -0.0070   0.8191   0.0132
  -9.250  -0.3743   0.10849   0.10634  -0.0082   0.8045   0.0134
  -9.000  -0.3649   0.10611   0.10390  -0.0087   0.7944   0.0136
  -8.750  -0.3556   0.10370   0.10145  -0.0097   0.7870   0.0138
  -8.500  -0.3463   0.10118   0.09891  -0.0110   0.7811   0.0142
  -8.250  -0.3373   0.09850   0.09620  -0.0124   0.7762   0.0146
  -8.000  -0.3283   0.09563   0.09331  -0.0141   0.7723   0.0153
  -7.750  -0.3210   0.09155   0.08923  -0.0183   0.7685   0.0167
  -7.500  -0.3118   0.08795   0.08562  -0.0219   0.7650   0.0168
  -7.250  -0.2980   0.08388   0.08153  -0.0263   0.7616   0.0168
  -7.000  -0.2867   0.07808   0.07570  -0.0318   0.7583   0.0171
  -6.750  -0.2706   0.07610   0.07371  -0.0329   0.7548   0.0174
  -6.500  -0.2523   0.07390   0.07149  -0.0353   0.7512   0.0179
  -6.250  -0.2322   0.07128   0.06884  -0.0387   0.7479   0.0186
  -6.000  -0.1997   0.06636   0.06385  -0.0483   0.7447   0.0212
  -5.750  -0.1710   0.06149   0.05894  -0.0554   0.7423   0.0213
  -4.500   0.0242   0.01712   0.01305  -0.1059   0.7315   0.0264
  -4.250   0.0531   0.01554   0.01115  -0.1067   0.7289   0.0269
  -4.000   0.0819   0.01320   0.00836  -0.1076   0.7268   0.0275
  -3.750   0.1101   0.01152   0.00640  -0.1081   0.7246   0.0286
  -3.500   0.1384   0.01093   0.00573  -0.1082   0.7224   0.0293
  -3.250   0.1668   0.01038   0.00507  -0.1082   0.7200   0.0298
  -3.000   0.1951   0.00991   0.00448  -0.1082   0.7174   0.0302
  -2.750   0.2234   0.00952   0.00397  -0.1082   0.7145   0.0306
  -2.500   0.2519   0.00915   0.00353  -0.1081   0.7119   0.0311
  -2.250   0.2804   0.00880   0.00313  -0.1081   0.7092   0.0317
  -2.000   0.3089   0.00854   0.00283  -0.1081   0.7065   0.0326
  -1.750   0.3373   0.00830   0.00254  -0.1080   0.7038   0.0333
  -1.500   0.3657   0.00812   0.00230  -0.1079   0.7008   0.0339
  -1.250   0.3940   0.00799   0.00212  -0.1078   0.6979   0.0343
  -1.000   0.4226   0.00777   0.00189  -0.1078   0.6951   0.0349
  -0.750   0.4511   0.00756   0.00166  -0.1077   0.6915   0.0362
  -0.500   0.4795   0.00742   0.00150  -0.1076   0.6880   0.0381
  -0.250   0.5078   0.00733   0.00139  -0.1075   0.6841   0.0408
   0.000   0.5363   0.00718   0.00129  -0.1075   0.6801   0.0512
   0.250   0.5647   0.00717   0.00143  -0.1074   0.6754   0.0823
   0.500   0.5929   0.00730   0.00155  -0.1073   0.6704   0.0877
   0.750   0.6212   0.00725   0.00152  -0.1072   0.6648   0.0912
   1.000   0.6496   0.00724   0.00154  -0.1071   0.6579   0.0943
   1.250   0.6778   0.00723   0.00153  -0.1071   0.6500   0.0969
   1.500   0.7059   0.00724   0.00152  -0.1070   0.6361   0.0995
   1.750   0.7338   0.00727   0.00150  -0.1068   0.6109   0.1008
   2.000   0.7604   0.00740   0.00142  -0.1066   0.5555   0.1034
   2.250   0.7869   0.00764   0.00150  -0.1063   0.5151   0.1059
   2.500   0.8138   0.00785   0.00161  -0.1062   0.4896   0.1087
   2.750   0.8410   0.00800   0.00170  -0.1060   0.4710   0.1110
   3.000   0.8683   0.00813   0.00178  -0.1059   0.4549   0.1125
   3.250   0.8956   0.00825   0.00187  -0.1058   0.4407   0.1138
   3.500   0.9230   0.00836   0.00195  -0.1057   0.4295   0.1156
   3.750   0.9503   0.00845   0.00204  -0.1056   0.4176   0.1181
   4.000   0.9777   0.00855   0.00213  -0.1054   0.4069   0.1204
   4.250   1.0049   0.00866   0.00225  -0.1053   0.3974   0.1228
   4.750   1.0591   0.00894   0.00250  -0.1050   0.3731   0.1288
   5.000   1.0860   0.00906   0.00265  -0.1049   0.3604   0.1422
   5.250   1.1109   0.00798   0.00304  -0.1048   0.3445   1.0000
   5.500   1.1370   0.00827   0.00323  -0.1045   0.3209   1.0000
   5.750   1.1625   0.00865   0.00346  -0.1042   0.2904   1.0000
   6.000   1.1870   0.00915   0.00376  -0.1038   0.2521   1.0000
   6.250   1.2094   0.00996   0.00423  -0.1032   0.1913   1.0000
   6.500   1.2306   0.01091   0.00484  -0.1024   0.1320   1.0000
   6.750   1.2546   0.01143   0.00526  -0.1019   0.1122   1.0000
   7.000   1.2791   0.01185   0.00562  -0.1015   0.0997   1.0000
   7.250   1.3034   0.01228   0.00599  -0.1010   0.0858   1.0000
   7.500   1.3262   0.01290   0.00646  -0.1004   0.0608   1.0000
   7.750   1.3458   0.01394   0.00725  -0.0994   0.0275   1.0000
   8.000   1.3680   0.01458   0.00786  -0.0986   0.0205   1.0000
   8.250   1.3903   0.01518   0.00848  -0.0978   0.0174   1.0000
   8.500   1.4132   0.01567   0.00900  -0.0971   0.0159   1.0000
   8.750   1.4345   0.01632   0.00968  -0.0962   0.0142   1.0000
   9.000   1.4549   0.01706   0.01048  -0.0952   0.0132   1.0000
   9.250   1.4764   0.01760   0.01107  -0.0943   0.0126   1.0000
   9.500   1.4970   0.01821   0.01173  -0.0934   0.0119   1.0000
   9.750   1.5166   0.01888   0.01245  -0.0923   0.0113   1.0000
  10.000   1.5341   0.01972   0.01334  -0.0910   0.0107   1.0000
  10.250   1.5433   0.02126   0.01501  -0.0885   0.0099   1.0000
  10.500   1.5620   0.02183   0.01562  -0.0874   0.0097   1.0000
  10.750   1.5782   0.02255   0.01640  -0.0859   0.0094   1.0000
  11.000   1.5898   0.02340   0.01733  -0.0837   0.0091   1.0000
  11.250   1.5995   0.02437   0.01838  -0.0814   0.0088   1.0000
  11.500   1.6086   0.02543   0.01952  -0.0793   0.0085   1.0000
  11.750   1.6168   0.02663   0.02078  -0.0773   0.0082   1.0000
  12.000   1.6240   0.02798   0.02221  -0.0754   0.0080   1.0000
  12.250   1.6288   0.02964   0.02394  -0.0736   0.0078   1.0000
  12.500   1.6287   0.03185   0.02625  -0.0717   0.0076   1.0000
  12.750   1.6211   0.03493   0.02947  -0.0696   0.0073   1.0000
  13.000   1.6143   0.03810   0.03278  -0.0679   0.0072   1.0000
  13.250   1.6194   0.04012   0.03491  -0.0670   0.0071   1.0000
  13.500   1.6231   0.04232   0.03721  -0.0661   0.0070   1.0000
  13.750   1.6249   0.04476   0.03975  -0.0653   0.0069   1.0000
  14.000   1.6246   0.04748   0.04257  -0.0645   0.0068   1.0000
  14.250   1.6228   0.05039   0.04560  -0.0638   0.0067   1.0000
  14.500   1.6204   0.05345   0.04877  -0.0632   0.0066   1.0000
  14.750   1.6172   0.05670   0.05213  -0.0628   0.0065   1.0000
  15.000   1.6135   0.06009   0.05563  -0.0627   0.0064   1.0000
  15.250   1.6097   0.06371   0.05936  -0.0628   0.0063   1.0000
  15.500   1.6051   0.06761   0.06337  -0.0633   0.0062   1.0000
  15.750   1.5995   0.07180   0.06768  -0.0640   0.0061   1.0000
  16.000   1.5940   0.07614   0.07213  -0.0650   0.0060   1.0000
  16.250   1.5869   0.08089   0.07699  -0.0662   0.0059   1.0000
  16.500   1.5789   0.08588   0.08210  -0.0676   0.0058   1.0000
  16.750   1.5704   0.09102   0.08736  -0.0692   0.0058   1.0000
  17.000   1.5609   0.09640   0.09285  -0.0710   0.0057   1.0000
  17.250   1.5502   0.10208   0.09864  -0.0730   0.0057   1.0000
  17.500   1.5394   0.10784   0.10451  -0.0752   0.0056   1.0000
  17.750   1.5278   0.11378   0.11056  -0.0775   0.0056   1.0000
  18.000   1.5153   0.12001   0.11691  -0.0801   0.0055   1.0000
  18.250   1.5031   0.12633   0.12334  -0.0829   0.0055   1.0000
  18.500   1.4912   0.13274   0.12986  -0.0859   0.0055   1.0000
  18.750   1.4791   0.13926   0.13649  -0.0891   0.0054   1.0000
  19.000   1.4668   0.14602   0.14336  -0.0926   0.0054   1.0000
  19.250   1.4547   0.15295   0.15040  -0.0964   0.0054   1.0000
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