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GOE 801 (MVA 301) AIRFOIL (goe801-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 801 (MVA 301) AIRFOIL (goe801-il)
Reynolds number: 500,000
Max Cl/Cd: 104.14 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe801-il-500000-n5.txt
Download as CSV file: xf-goe801-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1738   0.09214   0.08957  -0.0528   0.8919   0.0202
  -8.250  -0.1680   0.08892   0.08633  -0.0550   0.8828   0.0202
  -8.000  -0.1620   0.08570   0.08308  -0.0574   0.8744   0.0203
  -7.750  -0.1560   0.08241   0.07976  -0.0601   0.8656   0.0203
  -7.500  -0.1470   0.07863   0.07595  -0.0649   0.8577   0.0204
  -7.250  -0.1350   0.07596   0.07326  -0.0653   0.8508   0.0205
  -7.000  -0.1214   0.07378   0.07105  -0.0660   0.8444   0.0208
  -6.750  -0.1061   0.07133   0.06859  -0.0683   0.8370   0.0212
  -6.250  -0.0699   0.06532   0.06250  -0.0760   0.8229   0.0227
  -6.000  -0.0397   0.05990   0.05696  -0.0864   0.8156   0.0238
  -5.750  -0.0115   0.05518   0.05213  -0.0934   0.8086   0.0239
  -5.500   0.0183   0.05032   0.04713  -0.0998   0.8013   0.0240
  -5.250   0.0395   0.04708   0.04382  -0.1022   0.7945   0.0241
  -5.000   0.0606   0.04503   0.04172  -0.1034   0.7865   0.0243
  -4.750   0.0843   0.04291   0.03952  -0.1052   0.7786   0.0246
  -4.500   0.1103   0.04057   0.03708  -0.1073   0.7688   0.0251
  -4.250   0.1381   0.03803   0.03441  -0.1097   0.7576   0.0257
  -4.000   0.1807   0.03245   0.02837  -0.1148   0.7472   0.0281
  -3.750   0.2097   0.02924   0.02487  -0.1165   0.7352   0.0281
  -3.500   0.2376   0.02661   0.02198  -0.1176   0.7240   0.0282
  -3.000   0.2877   0.02353   0.01872  -0.1189   0.7001   0.0267
  -2.750   0.3172   0.02103   0.01590  -0.1197   0.6878   0.0259
  -2.500   0.3464   0.01900   0.01353  -0.1201   0.6755   0.0257
  -2.250   0.3749   0.01763   0.01188  -0.1203   0.6621   0.0262
  -2.000   0.4036   0.01613   0.01003  -0.1205   0.6482   0.0258
  -1.750   0.4321   0.01499   0.00858  -0.1205   0.6338   0.0257
  -1.250   0.4884   0.01355   0.00669  -0.1204   0.6068   0.0261
  -1.000   0.5164   0.01304   0.00600  -0.1204   0.5934   0.0263
  -0.750   0.5442   0.01263   0.00542  -0.1203   0.5802   0.0265
  -0.500   0.5719   0.01229   0.00494  -0.1201   0.5675   0.0268
   0.000   0.6275   0.01190   0.00432  -0.1199   0.5450   0.0278
   0.250   0.6551   0.01168   0.00402  -0.1198   0.5351   0.0280
   0.500   0.6827   0.01152   0.00379  -0.1197   0.5246   0.0281
   0.750   0.7102   0.01130   0.00353  -0.1196   0.5145   0.0284
   1.000   0.7375   0.01112   0.00332  -0.1196   0.5044   0.0288
   1.250   0.7651   0.01101   0.00320  -0.1195   0.4947   0.0293
   1.500   0.7926   0.01096   0.00313  -0.1194   0.4861   0.0298
   1.750   0.8200   0.01093   0.00309  -0.1194   0.4768   0.0305
   2.000   0.8475   0.01093   0.00307  -0.1193   0.4682   0.0312
   2.250   0.8747   0.01098   0.00309  -0.1192   0.4585   0.0325
   2.500   0.9019   0.01103   0.00311  -0.1191   0.4487   0.0332
   2.750   0.9287   0.01109   0.00312  -0.1189   0.4365   0.0342
   3.000   0.9552   0.01121   0.00318  -0.1187   0.4226   0.0354
   3.500   1.0080   0.01149   0.00335  -0.1183   0.3966   0.0390
   4.000   1.0558   0.01021   0.00385  -0.1173   0.3752   1.0000
   4.250   1.0821   0.01041   0.00399  -0.1170   0.3657   1.0000
   4.500   1.1080   0.01064   0.00415  -0.1167   0.3566   1.0000
   4.750   1.1336   0.01089   0.00433  -0.1164   0.3467   1.0000
   5.000   1.1591   0.01113   0.00453  -0.1161   0.3359   1.0000
   5.250   1.1840   0.01142   0.00474  -0.1157   0.3245   1.0000
   5.500   1.2089   0.01170   0.00496  -0.1152   0.3142   1.0000
   5.750   1.2343   0.01193   0.00518  -0.1149   0.3069   1.0000
   6.000   1.2592   0.01219   0.00541  -0.1145   0.2993   1.0000
   6.250   1.2842   0.01243   0.00564  -0.1141   0.2923   1.0000
   6.500   1.3087   0.01271   0.00590  -0.1137   0.2840   1.0000
   6.750   1.3330   0.01298   0.00616  -0.1132   0.2760   1.0000
   7.000   1.3565   0.01331   0.00646  -0.1126   0.2663   1.0000
   7.250   1.3798   0.01364   0.00676  -0.1120   0.2539   1.0000
   7.500   1.4006   0.01413   0.00715  -0.1110   0.2324   1.0000
   7.750   1.4183   0.01485   0.00767  -0.1096   0.2001   1.0000
   8.000   1.4345   0.01565   0.00828  -0.1080   0.1735   1.0000
   8.250   1.4523   0.01628   0.00884  -0.1066   0.1583   1.0000
   8.500   1.4701   0.01687   0.00938  -0.1051   0.1476   1.0000
   8.750   1.4874   0.01743   0.00991  -0.1036   0.1377   1.0000
   9.000   1.5032   0.01796   0.01044  -0.1018   0.1292   1.0000
   9.250   1.5176   0.01860   0.01105  -0.0999   0.1208   1.0000
   9.500   1.5334   0.01918   0.01163  -0.0982   0.1131   1.0000
   9.750   1.5471   0.01990   0.01232  -0.0963   0.1042   1.0000
  10.250   1.5680   0.02183   0.01412  -0.0920   0.0761   1.0000
  10.500   1.5769   0.02295   0.01518  -0.0899   0.0658   1.0000
  10.750   1.5870   0.02401   0.01624  -0.0879   0.0597   1.0000
  11.000   1.5967   0.02514   0.01738  -0.0861   0.0547   1.0000
  11.250   1.6071   0.02624   0.01852  -0.0844   0.0503   1.0000
  11.500   1.6145   0.02761   0.01990  -0.0825   0.0443   1.0000
  12.000   1.6126   0.03188   0.02407  -0.0779   0.0174   1.0000
  12.250   1.6166   0.03373   0.02599  -0.0762   0.0153   1.0000
  12.500   1.6220   0.03552   0.02787  -0.0749   0.0143   1.0000
  12.750   1.6258   0.03750   0.02995  -0.0735   0.0135   1.0000
  13.000   1.6281   0.03970   0.03225  -0.0722   0.0128   1.0000
  13.250   1.6313   0.04187   0.03452  -0.0711   0.0123   1.0000
  13.500   1.6348   0.04407   0.03682  -0.0702   0.0119   1.0000
  13.750   1.6369   0.04648   0.03933  -0.0694   0.0114   1.0000
  14.000   1.6379   0.04911   0.04207  -0.0687   0.0110   1.0000
  14.250   1.6376   0.05198   0.04505  -0.0681   0.0107   1.0000
  14.500   1.6358   0.05513   0.04831  -0.0678   0.0104   1.0000
  14.750   1.6323   0.05857   0.05187  -0.0675   0.0101   1.0000
  15.000   1.6268   0.06239   0.05581  -0.0675   0.0098   1.0000
  15.250   1.6225   0.06615   0.05969  -0.0676   0.0097   1.0000
  15.500   1.6190   0.06989   0.06354  -0.0678   0.0095   1.0000
  15.750   1.6140   0.07387   0.06764  -0.0682   0.0093   1.0000
  16.000   1.6078   0.07808   0.07198  -0.0687   0.0092   1.0000
  16.250   1.6006   0.08254   0.07656  -0.0694   0.0090   1.0000
  16.500   1.5926   0.08716   0.08130  -0.0702   0.0089   1.0000
  16.750   1.5836   0.09197   0.08622  -0.0712   0.0087   1.0000
  17.000   1.5742   0.09693   0.09131  -0.0723   0.0086   1.0000
  17.250   1.5643   0.10205   0.09654  -0.0736   0.0085   1.0000
  17.500   1.5542   0.10726   0.10187  -0.0750   0.0083   1.0000
  17.750   1.5439   0.11254   0.10726  -0.0766   0.0082   1.0000
  18.000   1.5335   0.11791   0.11274  -0.0783   0.0081   1.0000
  18.250   1.5231   0.12338   0.11833  -0.0802   0.0080   1.0000
  18.500   1.5126   0.12895   0.12400  -0.0823   0.0079   1.0000
  18.750   1.5016   0.13466   0.12982  -0.0847   0.0078   1.0000
  19.000   1.4907   0.14043   0.13569  -0.0871   0.0077   1.0000
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