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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.72 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe92-il-1000000-n5.txt
Download as CSV file: xf-goe92-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3118   0.12676   0.12495  -0.0142   0.8985   0.0042
 -10.500  -0.3052   0.12359   0.12175  -0.0154   0.8894   0.0042
 -10.250  -0.2986   0.12045   0.11857  -0.0165   0.8812   0.0042
 -10.000  -0.2919   0.11727   0.11536  -0.0178   0.8737   0.0042
  -9.750  -0.2852   0.11408   0.11214  -0.0191   0.8674   0.0042
  -9.500  -0.2783   0.11089   0.10894  -0.0204   0.8608   0.0042
  -9.250  -0.2714   0.10774   0.10575  -0.0217   0.8532   0.0042
  -9.000  -0.2645   0.10456   0.10256  -0.0231   0.8454   0.0042
  -8.750  -0.2575   0.10139   0.09937  -0.0245   0.8381   0.0042
  -8.500  -0.2505   0.09821   0.09617  -0.0259   0.8295   0.0042
  -8.250  -0.2435   0.09502   0.09296  -0.0274   0.8207   0.0042
  -8.000  -0.2367   0.09201   0.08992  -0.0287   0.8102   0.0041
  -7.750  -0.2293   0.08912   0.08701  -0.0303   0.7983   0.0040
  -7.500  -0.2216   0.08594   0.08379  -0.0323   0.7858   0.0040
  -7.250  -0.2137   0.08269   0.08051  -0.0347   0.7718   0.0040
  -7.000  -0.2023   0.07917   0.07694  -0.0383   0.7550   0.0040
  -6.750  -0.1877   0.07545   0.07313  -0.0426   0.7304   0.0040
  -6.500  -0.1698   0.07082   0.06835  -0.0485   0.6927   0.0043
  -6.250  -0.1532   0.06838   0.06571  -0.0516   0.6459   0.0046
  -6.000  -0.1337   0.06589   0.06308  -0.0551   0.6160   0.0050
  -5.500  -0.0832   0.05566   0.05263  -0.0675   0.5850   0.0042
  -5.250  -0.0568   0.05153   0.04839  -0.0723   0.5722   0.0041
  -5.000  -0.0285   0.04715   0.04387  -0.0769   0.5606   0.0041
  -4.750   0.0019   0.04221   0.03876  -0.0814   0.5497   0.0041
  -4.500   0.0334   0.03682   0.03316  -0.0853   0.5401   0.0044
  -4.250   0.0615   0.03408   0.03025  -0.0871   0.5291   0.0046
  -4.000   0.0903   0.03106   0.02702  -0.0886   0.5182   0.0049
  -3.750   0.1203   0.02698   0.02266  -0.0899   0.5083   0.0053
  -3.500   0.1521   0.01767   0.01245  -0.0905   0.5026   0.0069
  -3.250   0.1795   0.01632   0.01086  -0.0904   0.4897   0.0075
  -3.000   0.2069   0.01418   0.00835  -0.0902   0.4763   0.0086
  -2.750   0.2338   0.01161   0.00530  -0.0898   0.4622   0.0107
  -2.500   0.2613   0.01177   0.00539  -0.0898   0.4448   0.0119
  -2.250   0.2884   0.01096   0.00437  -0.0896   0.4280   0.0140
  -2.000   0.3160   0.01128   0.00462  -0.0896   0.4085   0.0146
  -1.750   0.3435   0.01150   0.00473  -0.0896   0.3895   0.0157
  -1.500   0.3708   0.01136   0.00444  -0.0895   0.3741   0.0180
  -1.250   0.3983   0.01125   0.00419  -0.0894   0.3616   0.0195
  -1.000   0.4260   0.01146   0.00430  -0.0893   0.3491   0.0201
  -0.750   0.4528   0.01087   0.00362  -0.0893   0.3390   0.0214
  -0.500   0.4802   0.01081   0.00350  -0.0892   0.3302   0.0223
  -0.250   0.5078   0.01073   0.00339  -0.0892   0.3251   0.0235
   0.000   0.5354   0.01056   0.00317  -0.0892   0.3202   0.0241
   0.250   0.5628   0.01042   0.00297  -0.0892   0.3151   0.0246
   0.500   0.5903   0.01027   0.00278  -0.0891   0.3108   0.0248
   0.750   0.6179   0.01017   0.00265  -0.0891   0.3069   0.0253
   1.000   0.6454   0.01007   0.00251  -0.0891   0.3026   0.0255
   1.250   0.6728   0.00999   0.00239  -0.0891   0.2988   0.0253
   1.500   0.7006   0.00991   0.00229  -0.0891   0.2966   0.0253
   1.750   0.7283   0.00986   0.00222  -0.0891   0.2943   0.0255
   2.000   0.7560   0.00983   0.00217  -0.0892   0.2917   0.0259
   2.250   0.7835   0.00984   0.00216  -0.0892   0.2882   0.0266
   2.500   0.8109   0.00990   0.00219  -0.0892   0.2844   0.0277
   2.750   0.8385   0.00995   0.00225  -0.0892   0.2822   0.0285
   3.000   0.8661   0.00996   0.00226  -0.0892   0.2800   0.0301
   3.250   0.8935   0.01001   0.00231  -0.0893   0.2771   0.0315
   3.500   0.9209   0.01008   0.00238  -0.0893   0.2740   0.0326
   3.750   0.9481   0.01017   0.00246  -0.0893   0.2710   0.0337
   4.000   0.9753   0.01026   0.00256  -0.0893   0.2685   0.0360
   4.250   1.0026   0.01033   0.00266  -0.0893   0.2659   0.0375
   4.750   1.0535   0.00903   0.00313  -0.0892   0.2529   1.0000
   5.000   1.0797   0.00925   0.00328  -0.0891   0.2403   1.0000
   5.250   1.1053   0.00953   0.00346  -0.0889   0.2216   1.0000
   5.500   1.1218   0.01089   0.00426  -0.0876   0.1317   1.0000
   5.750   1.1455   0.01140   0.00465  -0.0871   0.1115   1.0000
   6.000   1.1698   0.01181   0.00500  -0.0868   0.0982   1.0000
   6.250   1.1861   0.01320   0.00600  -0.0853   0.0193   1.0000
   6.500   1.2111   0.01349   0.00632  -0.0851   0.0130   1.0000
   6.750   1.2356   0.01384   0.00670  -0.0847   0.0105   1.0000
   7.000   1.2597   0.01422   0.00712  -0.0843   0.0082   1.0000
   7.250   1.2837   0.01457   0.00750  -0.0839   0.0070   1.0000
   7.500   1.3069   0.01502   0.00798  -0.0834   0.0059   1.0000
   7.750   1.3299   0.01545   0.00845  -0.0829   0.0053   1.0000
   8.000   1.3529   0.01587   0.00891  -0.0824   0.0046   1.0000
   8.250   1.3750   0.01635   0.00941  -0.0818   0.0041   1.0000
   8.500   1.3956   0.01696   0.01009  -0.0809   0.0037   1.0000
   8.750   1.4164   0.01750   0.01069  -0.0801   0.0034   1.0000
   9.000   1.4363   0.01810   0.01135  -0.0792   0.0031   1.0000
   9.250   1.4553   0.01874   0.01205  -0.0781   0.0029   1.0000
   9.500   1.4735   0.01939   0.01278  -0.0770   0.0027   1.0000
   9.750   1.4902   0.02011   0.01355  -0.0757   0.0025   1.0000
  10.000   1.5023   0.02110   0.01463  -0.0737   0.0023   1.0000
  10.250   1.5146   0.02185   0.01546  -0.0717   0.0022   1.0000
  10.500   1.5235   0.02282   0.01652  -0.0693   0.0021   1.0000
  10.750   1.5304   0.02396   0.01777  -0.0670   0.0020   1.0000
  11.000   1.5359   0.02529   0.01921  -0.0647   0.0019   1.0000
  11.250   1.5404   0.02680   0.02082  -0.0628   0.0018   1.0000
  11.500   1.5436   0.02851   0.02264  -0.0609   0.0017   1.0000
  11.750   1.5455   0.03045   0.02469  -0.0593   0.0017   1.0000
  12.000   1.5468   0.03259   0.02693  -0.0580   0.0016   1.0000
  12.250   1.5465   0.03501   0.02948  -0.0569   0.0016   1.0000
  12.500   1.5460   0.03764   0.03221  -0.0562   0.0015   1.0000
  12.750   1.5436   0.04067   0.03535  -0.0559   0.0015   1.0000
  13.000   1.5381   0.04434   0.03914  -0.0560   0.0015   1.0000
  13.250   1.5326   0.04829   0.04321  -0.0565   0.0014   1.0000
  13.500   1.5221   0.05310   0.04815  -0.0574   0.0014   1.0000
  13.750   1.5103   0.05821   0.05339  -0.0585   0.0014   1.0000
  14.000   1.4967   0.06360   0.05891  -0.0597   0.0014   1.0000
  14.250   1.4816   0.06930   0.06473  -0.0610   0.0013   1.0000
  14.500   1.4656   0.07522   0.07077  -0.0624   0.0013   1.0000
  14.750   1.4489   0.08122   0.07689  -0.0639   0.0013   1.0000
  15.000   1.4330   0.08724   0.08302  -0.0654   0.0013   1.0000
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