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SA7026 (sa7026-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 1,000,000
Max Cl/Cd: 143.09 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7026-il-1000000.txt
Download as CSV file: xf-sa7026-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3723   0.14212   0.14037  -0.0284   1.0000   0.0057
 -12.500  -0.3666   0.13892   0.13718  -0.0295   1.0000   0.0060
  -8.500  -0.2725   0.07967   0.07811  -0.0608   0.9828   0.0080
  -8.250  -0.2552   0.07668   0.07512  -0.0648   0.9786   0.0084
  -8.000  -0.2371   0.07212   0.07054  -0.0712   0.9735   0.0085
  -7.750  -0.2203   0.06820   0.06661  -0.0768   0.9652   0.0091
  -7.500  -0.2148   0.06420   0.06258  -0.0810   0.9516   0.0092
  -7.250  -0.2104   0.06025   0.05859  -0.0850   0.9394   0.0094
  -7.000  -0.2050   0.05592   0.05420  -0.0892   0.9289   0.0096
  -6.750  -0.1975   0.05085   0.04906  -0.0939   0.9193   0.0099
  -6.500  -0.1867   0.04536   0.04345  -0.0981   0.9112   0.0101
  -6.250  -0.1722   0.03959   0.03750  -0.1012   0.9042   0.0108
  -6.000  -0.1505   0.03547   0.03318  -0.1023   0.8987   0.0114
  -5.750  -0.1332   0.03134   0.02875  -0.1032   0.8924   0.0115
  -5.500  -0.1238   0.02390   0.02069  -0.1041   0.8859   0.0120
  -5.250  -0.1038   0.02099   0.01752  -0.1042   0.8802   0.0126
  -5.000  -0.0801   0.01956   0.01593  -0.1042   0.8755   0.0131
  -4.750  -0.0554   0.01820   0.01440  -0.1041   0.8708   0.0138
  -4.500  -0.0298   0.01687   0.01286  -0.1039   0.8658   0.0150
  -4.250  -0.0027   0.01625   0.01205  -0.1036   0.8614   0.0166
  -4.000   0.0224   0.01214   0.00730  -0.1024   0.8564   0.0122
  -3.750   0.0488   0.01062   0.00563  -0.1019   0.8512   0.0106
  -3.500   0.0757   0.00988   0.00474  -0.1015   0.8462   0.0110
  -3.250   0.1031   0.00941   0.00422  -0.1013   0.8402   0.0114
  -3.000   0.1304   0.00902   0.00375  -0.1011   0.8345   0.0116
  -2.750   0.1571   0.00833   0.00296  -0.1009   0.8290   0.0118
  -2.500   0.1843   0.00781   0.00234  -0.1007   0.8231   0.0124
  -2.250   0.2120   0.00753   0.00197  -0.1006   0.8177   0.0126
  -2.000   0.2400   0.00729   0.00167  -0.1005   0.8113   0.0129
  -1.750   0.2678   0.00713   0.00142  -0.1004   0.8053   0.0139
  -1.500   0.2959   0.00697   0.00124  -0.1003   0.7982   0.0183
  -1.250   0.3225   0.00648   0.00109  -0.1003   0.7909   0.1342
  -1.000   0.3495   0.00608   0.00102  -0.1003   0.7825   0.2501
  -0.750   0.3761   0.00570   0.00100  -0.1003   0.7750   0.3870
  -0.500   0.4024   0.00534   0.00101  -0.1002   0.7667   0.5254
  -0.250   0.4277   0.00495   0.00104  -0.0998   0.7585   0.6843
   0.000   0.4500   0.00457   0.00108  -0.0985   0.7500   0.8416
   0.250   0.4887   0.00432   0.00106  -0.1005   0.7409   0.9862
   0.500   0.5203   0.00437   0.00104  -0.1014   0.7310   1.0000
   0.750   0.5471   0.00444   0.00104  -0.1011   0.7197   1.0000
   1.000   0.5738   0.00453   0.00105  -0.1009   0.7073   1.0000
   1.250   0.6006   0.00461   0.00106  -0.1007   0.6943   1.0000
   1.500   0.6274   0.00470   0.00109  -0.1004   0.6808   1.0000
   2.000   0.6807   0.00491   0.00117  -0.1000   0.6517   1.0000
   2.250   0.7073   0.00503   0.00123  -0.0997   0.6361   1.0000
   2.500   0.7337   0.00516   0.00130  -0.0995   0.6193   1.0000
   2.750   0.7598   0.00531   0.00138  -0.0992   0.6006   1.0000
   3.000   0.7856   0.00550   0.00148  -0.0988   0.5782   1.0000
   3.250   0.8109   0.00571   0.00158  -0.0984   0.5534   1.0000
   3.500   0.8366   0.00590   0.00170  -0.0980   0.5312   1.0000
   3.750   0.8620   0.00612   0.00183  -0.0976   0.5086   1.0000
   4.000   0.8873   0.00635   0.00199  -0.0972   0.4863   1.0000
   4.250   0.9125   0.00659   0.00214  -0.0968   0.4628   1.0000
   4.500   0.9372   0.00685   0.00232  -0.0964   0.4373   1.0000
   4.750   0.9607   0.00722   0.00253  -0.0957   0.4019   1.0000
   5.000   0.9840   0.00761   0.00277  -0.0950   0.3642   1.0000
   5.250   1.0070   0.00802   0.00302  -0.0943   0.3283   1.0000
   5.500   1.0292   0.00850   0.00330  -0.0935   0.2889   1.0000
   5.750   1.0505   0.00905   0.00363  -0.0925   0.2431   1.0000
   6.000   1.0721   0.00958   0.00398  -0.0916   0.2059   1.0000
   6.250   1.0927   0.01017   0.00437  -0.0906   0.1657   1.0000
   6.500   1.1124   0.01084   0.00481  -0.0894   0.1236   1.0000
   6.750   1.1310   0.01159   0.00532  -0.0881   0.0820   1.0000
   7.000   1.1475   0.01252   0.00597  -0.0864   0.0390   1.0000
   7.250   1.1632   0.01351   0.00675  -0.0845   0.0085   1.0000
   7.500   1.1841   0.01403   0.00730  -0.0834   0.0061   1.0000
   7.750   1.2053   0.01449   0.00782  -0.0824   0.0056   1.0000
   8.000   1.2253   0.01504   0.00844  -0.0811   0.0051   1.0000
   8.250   1.2447   0.01561   0.00908  -0.0798   0.0048   1.0000
   8.500   1.2631   0.01622   0.00976  -0.0783   0.0047   1.0000
   8.750   1.2802   0.01689   0.01050  -0.0766   0.0046   1.0000
   9.000   1.2946   0.01760   0.01131  -0.0744   0.0046   1.0000
   9.250   1.3065   0.01837   0.01217  -0.0719   0.0044   1.0000
   9.500   1.3175   0.01920   0.01309  -0.0692   0.0044   1.0000
   9.750   1.3274   0.02011   0.01408  -0.0666   0.0042   1.0000
  10.000   1.3353   0.02118   0.01523  -0.0638   0.0041   1.0000
  10.250   1.3421   0.02235   0.01651  -0.0610   0.0040   1.0000
  10.500   1.3491   0.02356   0.01781  -0.0584   0.0040   1.0000
  10.750   1.3544   0.02495   0.01930  -0.0557   0.0039   1.0000
  11.000   1.3585   0.02652   0.02097  -0.0531   0.0039   1.0000
  11.250   1.3621   0.02820   0.02277  -0.0506   0.0038   1.0000
  11.500   1.3661   0.02996   0.02463  -0.0483   0.0038   1.0000
  11.750   1.3658   0.03229   0.02710  -0.0458   0.0037   1.0000
  12.000   1.3721   0.03395   0.02889  -0.0441   0.0038   1.0000
  12.250   1.3719   0.03652   0.03161  -0.0421   0.0037   1.0000
  12.500   1.3722   0.03914   0.03438  -0.0403   0.0037   1.0000
  12.750   1.3734   0.04161   0.03698  -0.0388   0.0037   1.0000
  13.000   1.3664   0.04547   0.04107  -0.0371   0.0037   1.0000
  13.250   1.3504   0.05083   0.04673  -0.0354   0.0036   1.0000
  13.500   1.3448   0.05425   0.05031  -0.0347   0.0036   1.0000
  13.750   1.3502   0.05590   0.05200  -0.0346   0.0037   1.0000
  14.000   1.3409   0.06010   0.05638  -0.0345   0.0037   1.0000
  14.250   1.3122   0.06767   0.06426  -0.0352   0.0036   1.0000
  14.500   1.3125   0.07066   0.06733  -0.0361   0.0037   1.0000
  14.750   1.2898   0.07791   0.07481  -0.0382   0.0036   1.0000
  15.000   1.2880   0.08177   0.07876  -0.0399   0.0037   1.0000
  15.250   1.2809   0.08685   0.08396  -0.0423   0.0037   1.0000
  15.500   1.2660   0.09376   0.09102  -0.0456   0.0037   1.0000
  15.750   1.2518   0.10091   0.09832  -0.0494   0.0037   1.0000
  16.000   1.2435   0.10716   0.10469  -0.0531   0.0038   1.0000
  16.250   1.2272   0.11547   0.11316  -0.0579   0.0038   1.0000
  16.500   1.2146   0.12336   0.12118  -0.0628   0.0038   1.0000
  16.750   1.2027   0.13143   0.12937  -0.0678   0.0038   1.0000
  17.000   1.1888   0.14042   0.13851  -0.0735   0.0039   1.0000
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