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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 175.05 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802a-il-1000000-n5.txt
Download as CSV file: xf-goe802a-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2426   0.10228   0.10033  -0.0410   0.8838   0.0092
  -9.750  -0.2356   0.09930   0.09731  -0.0424   0.8754   0.0097
  -9.500  -0.2370   0.09362   0.09159  -0.0453   0.8677   0.0105
  -9.250  -0.2278   0.09121   0.08917  -0.0467   0.8598   0.0106
  -9.000  -0.2182   0.08893   0.08685  -0.0482   0.8522   0.0107
  -8.750  -0.2081   0.08657   0.08448  -0.0499   0.8453   0.0108
  -8.500  -0.1983   0.08416   0.08205  -0.0517   0.8377   0.0110
  -8.250  -0.1873   0.08158   0.07943  -0.0542   0.8310   0.0112
  -8.000  -0.1729   0.07864   0.07648  -0.0577   0.8239   0.0114
  -7.750  -0.1572   0.07561   0.07341  -0.0614   0.8169   0.0119
  -7.500  -0.1401   0.07190   0.06966  -0.0661   0.8110   0.0125
  -7.250  -0.1202   0.06557   0.06328  -0.0743   0.8043   0.0133
  -7.000  -0.0995   0.06315   0.06080  -0.0775   0.7971   0.0135
  -6.750  -0.0776   0.06066   0.05827  -0.0808   0.7907   0.0136
  -6.500  -0.0545   0.05802   0.05559  -0.0842   0.7834   0.0138
  -6.250  -0.0306   0.05532   0.05280  -0.0876   0.7761   0.0141
  -6.000  -0.0054   0.05252   0.04994  -0.0911   0.7690   0.0147
  -5.750   0.0213   0.04916   0.04648  -0.0949   0.7604   0.0153
  -5.500   0.0558   0.04277   0.03987  -0.1014   0.7525   0.0164
  -5.250   0.0807   0.04069   0.03768  -0.1032   0.7396   0.0165
  -5.000   0.1060   0.03900   0.03589  -0.1047   0.7248   0.0167
  -4.750   0.1318   0.03732   0.03408  -0.1061   0.7101   0.0169
  -4.500   0.1581   0.03572   0.03236  -0.1074   0.6973   0.0173
  -4.250   0.1856   0.03373   0.03023  -0.1088   0.6843   0.0178
  -4.000   0.2137   0.03149   0.02782  -0.1102   0.6709   0.0182
  -3.750   0.2420   0.02931   0.02544  -0.1114   0.6570   0.0187
  -3.500   0.2706   0.02713   0.02305  -0.1123   0.6437   0.0190
  -3.250   0.2994   0.02499   0.02068  -0.1131   0.6312   0.0192
  -3.000   0.3287   0.02241   0.01777  -0.1138   0.6181   0.0199
  -2.500   0.3826   0.02044   0.01548  -0.1146   0.5878   0.0203
  -2.250   0.4097   0.01972   0.01463  -0.1149   0.5747   0.0206
  -2.000   0.4371   0.01895   0.01371  -0.1153   0.5630   0.0209
  -1.750   0.4648   0.01810   0.01272  -0.1156   0.5523   0.0212
  -1.500   0.4925   0.01725   0.01170  -0.1158   0.5422   0.0216
  -1.250   0.5205   0.01635   0.01063  -0.1161   0.5317   0.0218
  -1.000   0.5483   0.01546   0.00956  -0.1163   0.5216   0.0219
  -0.500   0.6034   0.01168   0.00505  -0.1167   0.5035   0.0232
  -0.250   0.6300   0.01099   0.00424  -0.1169   0.4953   0.0236
   0.000   0.6566   0.01069   0.00386  -0.1171   0.4864   0.0238
   0.250   0.6836   0.01026   0.00336  -0.1173   0.4789   0.0243
   0.500   0.7107   0.01012   0.00318  -0.1174   0.4700   0.0247
   0.750   0.7379   0.01001   0.00305  -0.1176   0.4622   0.0250
   1.000   0.7651   0.00994   0.00296  -0.1176   0.4524   0.0253
   1.250   0.7922   0.00992   0.00291  -0.1177   0.4430   0.0258
   1.500   0.8193   0.00991   0.00288  -0.1178   0.4326   0.0265
   1.750   0.8464   0.00993   0.00287  -0.1178   0.4229   0.0271
   2.000   0.8732   0.01002   0.00291  -0.1178   0.4094   0.0276
   2.250   0.8999   0.01014   0.00297  -0.1177   0.3928   0.0281
   2.500   0.9263   0.01029   0.00305  -0.1177   0.3762   0.0285
   2.750   0.9533   0.01048   0.00320  -0.1176   0.3648   0.0297
   3.000   0.9801   0.01059   0.00330  -0.1175   0.3562   0.0309
   3.250   1.0067   0.01067   0.00338  -0.1175   0.3487   0.0322
   3.750   1.0598   0.01100   0.00374  -0.1174   0.3308   0.0472
   4.000   1.0858   0.01109   0.00380  -0.1174   0.3214   0.0605
   4.250   1.1112   0.01124   0.00391  -0.1172   0.3091   0.0642
   4.500   1.1366   0.01151   0.00411  -0.1170   0.2952   0.0660
   4.750   1.1628   0.01161   0.00422  -0.1169   0.2874   0.0678
   5.000   1.1882   0.01178   0.00436  -0.1168   0.2793   0.0700
   5.250   1.2144   0.01194   0.00453  -0.1166   0.2727   0.0734
   5.500   1.2396   0.01209   0.00467  -0.1165   0.2636   0.0742
   6.000   1.2891   0.01244   0.00497  -0.1160   0.2422   0.0750
   6.250   1.3133   0.01267   0.00516  -0.1156   0.2278   0.0757
   6.500   1.3359   0.01302   0.00543  -0.1150   0.2080   0.0761
   6.750   1.3559   0.01358   0.00582  -0.1141   0.1780   0.0764
   7.000   1.3761   0.01411   0.00623  -0.1131   0.1563   0.0769
   7.250   1.3986   0.01443   0.00653  -0.1125   0.1458   0.0775
   7.500   1.4202   0.01479   0.00686  -0.1118   0.1348   0.0780
   8.000   1.4626   0.01555   0.00755  -0.1102   0.1145   0.0792
   8.250   1.4827   0.01597   0.00794  -0.1092   0.1045   0.0797
   8.500   1.5010   0.01649   0.00839  -0.1079   0.0913   0.0802
   8.750   1.5159   0.01721   0.00899  -0.1061   0.0716   0.0813
   9.250   1.5456   0.01827   0.01001  -0.1023   0.0578   0.0845
   9.500   1.5595   0.01877   0.01053  -0.1002   0.0528   0.0846
   9.750   1.5019   0.00858   0.00073  -0.0876   0.0505   0.0847
  10.000   1.5114   0.00913   0.00130  -0.0854   0.0455   0.0851
  10.250   1.5218   0.00969   0.00189  -0.0834   0.0413   0.0861
  10.500   1.5219   0.01081   0.00295  -0.0802   0.0269   0.0863
  10.750   1.5194   0.01222   0.00437  -0.0770   0.0154   0.0864
  11.000   1.5263   0.01320   0.00541  -0.0750   0.0139   0.0865
  11.250   1.5325   0.01431   0.00658  -0.0730   0.0127   0.0865
  11.500   1.5385   0.01551   0.00786  -0.0711   0.0117   0.0865
  11.750   1.5458   0.01671   0.00913  -0.0695   0.0113   0.0870
  12.000   1.5512   0.01812   0.01062  -0.0678   0.0109   0.0874
  12.250   1.5554   0.01975   0.01233  -0.0661   0.0104   0.0876
  12.500   1.5581   0.02163   0.01429  -0.0644   0.0098   0.0878
  12.750   1.5590   0.02377   0.01651  -0.0627   0.0094   0.0879
  13.000   1.5585   0.02622   0.01904  -0.0610   0.0090   0.0879
  13.250   1.5571   0.02892   0.02183  -0.0595   0.0086   0.0879
  13.500   1.5567   0.03160   0.02460  -0.0581   0.0084   0.0880
  14.000   1.5535   0.03775   0.03092  -0.0559   0.0081   0.0883
  14.250   1.5493   0.04129   0.03456  -0.0548   0.0079   0.0885
  14.500   1.5440   0.04510   0.03846  -0.0539   0.0077   0.0887
  14.750   1.5378   0.04917   0.04263  -0.0531   0.0076   0.0889
  15.000   1.5297   0.05350   0.04707  -0.0523   0.0074   0.0891
  15.250   1.5208   0.05802   0.05169  -0.0517   0.0073   0.0892
  15.500   1.5113   0.06270   0.05646  -0.0513   0.0071   0.0893
  15.750   1.5001   0.06754   0.06141  -0.0509   0.0070   0.0893
  16.000   1.4890   0.07240   0.06637  -0.0508   0.0069   0.0893
  16.500   1.4636   0.08232   0.07649  -0.0508   0.0067   0.0894
  16.750   1.4500   0.08730   0.08158  -0.0511   0.0066   0.0894
  17.000   1.4352   0.09228   0.08666  -0.0514   0.0065   0.0895
  17.250   1.4198   0.09725   0.09174  -0.0520   0.0064   0.0895
  17.500   1.4033   0.10223   0.09683  -0.0527   0.0062   0.0896
  17.750   1.3858   0.10711   0.10182  -0.0535   0.0062   0.0897
  18.000   1.3681   0.11183   0.10666  -0.0544   0.0061   0.0898
  18.250   1.3506   0.11614   0.11109  -0.0553   0.0061   0.0899
  18.500   1.3236   0.11993   0.11501  -0.0558   0.0061   0.0899
  18.750   1.3012   0.12356   0.11876  -0.0565   0.0060   0.0900
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