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GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 492 AIRFOIL (goe492-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.5 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe492-il-1000000-n5.txt
Download as CSV file: xf-goe492-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 492 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4078   0.09653   0.09492  -0.0290   1.0000   0.0025
  -8.750  -0.4073   0.09283   0.09125  -0.0297   1.0000   0.0033
  -8.500  -0.4081   0.09004   0.08848  -0.0299   1.0000   0.0031
  -8.000  -0.3933   0.08159   0.08006  -0.0367   0.9964   0.0030
  -7.750  -0.3826   0.07719   0.07566  -0.0415   0.9902   0.0030
  -7.500  -0.3691   0.07159   0.07007  -0.0486   0.9826   0.0029
  -7.000  -0.3287   0.01863   0.01564  -0.1031   0.9526   0.0022
  -6.750  -0.3057   0.01548   0.01195  -0.1036   0.9447   0.0022
  -6.500  -0.2804   0.01367   0.00978  -0.1038   0.9385   0.0022
  -6.250  -0.2549   0.01253   0.00840  -0.1037   0.9316   0.0024
  -6.000  -0.2288   0.01156   0.00717  -0.1036   0.9251   0.0026
  -5.750  -0.2030   0.01071   0.00612  -0.1034   0.9181   0.0028
  -5.500  -0.1766   0.01004   0.00526  -0.1032   0.9125   0.0031
  -5.250  -0.1502   0.00954   0.00462  -0.1030   0.9068   0.0034
  -5.000  -0.1238   0.00893   0.00385  -0.1028   0.9016   0.0037
  -4.750  -0.0973   0.00849   0.00333  -0.1026   0.8965   0.0043
  -4.500  -0.0704   0.00821   0.00297  -0.1025   0.8909   0.0052
  -4.250  -0.0434   0.00794   0.00261  -0.1024   0.8860   0.0058
  -4.000  -0.0165   0.00755   0.00213  -0.1022   0.8807   0.0076
  -3.750   0.0105   0.00733   0.00183  -0.1020   0.8750   0.0097
  -3.500   0.0375   0.00710   0.00161  -0.1019   0.8695   0.0202
  -3.250   0.0648   0.00700   0.00149  -0.1018   0.8633   0.0287
  -3.000   0.0920   0.00690   0.00137  -0.1017   0.8574   0.0325
  -2.750   0.1191   0.00681   0.00127  -0.1016   0.8498   0.0362
  -2.500   0.1460   0.00678   0.00117  -0.1014   0.8386   0.0383
  -2.250   0.1725   0.00667   0.00098  -0.1011   0.8246   0.0413
  -2.000   0.1992   0.00659   0.00086  -0.1008   0.8107   0.0448
  -1.750   0.2260   0.00654   0.00075  -0.1006   0.7985   0.0478
  -1.500   0.2527   0.00651   0.00066  -0.1004   0.7852   0.0504
  -1.250   0.2793   0.00647   0.00059  -0.1001   0.7703   0.0588
  -1.000   0.3055   0.00638   0.00053  -0.0998   0.7529   0.0885
  -0.750   0.3310   0.00617   0.00047  -0.0995   0.7332   0.1726
  -0.500   0.3567   0.00613   0.00048  -0.0991   0.7095   0.2219
  -0.250   0.3820   0.00623   0.00051  -0.0986   0.6802   0.2419
   0.000   0.4081   0.00631   0.00053  -0.0983   0.6605   0.2546
   0.250   0.4346   0.00637   0.00057  -0.0981   0.6449   0.2662
   0.500   0.4611   0.00642   0.00061  -0.0979   0.6314   0.2782
   0.750   0.4877   0.00646   0.00066  -0.0977   0.6194   0.2933
   1.000   0.5145   0.00650   0.00071  -0.0975   0.6081   0.3064
   1.250   0.5414   0.00652   0.00077  -0.0974   0.5981   0.3187
   1.500   0.5673   0.00663   0.00083  -0.0970   0.5772   0.3294
   1.750   0.5927   0.00673   0.00093  -0.0966   0.5465   0.3531
   2.000   0.6160   0.00645   0.00108  -0.0961   0.5103   0.5833
   2.250   0.6351   0.00671   0.00133  -0.0946   0.4174   0.7215
   2.500   0.6538   0.00704   0.00159  -0.0930   0.3294   0.8251
   2.750   0.6768   0.00828   0.00222  -0.0928   0.1043   1.0000
   3.000   0.7000   0.00880   0.00248  -0.0921   0.0400   1.0000
   3.250   0.7245   0.00916   0.00273  -0.0915   0.0147   1.0000
   3.500   0.7500   0.00942   0.00299  -0.0911   0.0089   1.0000
   3.750   0.7754   0.00967   0.00328  -0.0906   0.0073   1.0000
   4.000   0.7997   0.01007   0.00372  -0.0900   0.0056   1.0000
   4.250   0.8244   0.01040   0.00409  -0.0894   0.0050   1.0000
   4.500   0.8493   0.01069   0.00439  -0.0889   0.0042   1.0000
   4.750   0.8733   0.01109   0.00483  -0.0882   0.0036   1.0000
   5.000   0.8951   0.01178   0.00561  -0.0871   0.0032   1.0000
   5.250   0.9182   0.01229   0.00618  -0.0862   0.0030   1.0000
   5.500   0.9401   0.01295   0.00694  -0.0851   0.0027   1.0000
   5.750   0.9610   0.01375   0.00784  -0.0838   0.0024   1.0000
   6.000   0.9811   0.01473   0.00892  -0.0824   0.0023   1.0000
   6.250   1.0010   0.01589   0.01020  -0.0809   0.0022   1.0000
   6.500   1.0229   0.01675   0.01119  -0.0799   0.0021   1.0000
   6.750   1.0452   0.01746   0.01196  -0.0791   0.0020   1.0000
   7.000   1.0645   0.01932   0.01403  -0.0776   0.0017   1.0000
   7.250   1.0855   0.02111   0.01606  -0.0764   0.0017   1.0000
   7.500   1.1040   0.02486   0.02023  -0.0742   0.0016   1.0000
   7.750   1.1128   0.03367   0.02976  -0.0693   0.0013   1.0000
   8.000   1.1191   0.03944   0.03597  -0.0653   0.0012   1.0000
   8.250   1.1220   0.04492   0.04181  -0.0615   0.0011   1.0000
   8.500   1.1224   0.05022   0.04741  -0.0579   0.0011   1.0000
   8.750   1.1191   0.05536   0.05282  -0.0544   0.0012   1.0000
   9.000   1.1130   0.06006   0.05773  -0.0512   0.0012   1.0000
   9.250   1.1028   0.06452   0.06239  -0.0480   0.0012   1.0000
   9.500   1.0865   0.06830   0.06631  -0.0443   0.0012   1.0000
   9.750   1.0672   0.07153   0.06965  -0.0410   0.0012   1.0000
  10.000   1.0462   0.07535   0.07358  -0.0392   0.0012   1.0000
  10.250   1.0261   0.07972   0.07805  -0.0392   0.0013   1.0000
  10.500   1.0043   0.08522   0.08365  -0.0410   0.0013   1.0000
  10.750   0.9843   0.09173   0.09024  -0.0450   0.0013   1.0000
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