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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 50,000
Max Cl/Cd: 34.6 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s826-nr-50000.txt
Download as CSV file: xf-s826-nr-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S826 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3255   0.12124   0.11481  -0.0285   1.0000   0.2981
  -8.750  -0.3273   0.11953   0.11319  -0.0269   1.0000   0.3129
  -8.500  -0.3272   0.11762   0.11136  -0.0252   1.0000   0.3274
  -8.000  -0.3187   0.11259   0.10648  -0.0216   1.0000   0.3567
  -7.750  -0.3246   0.11141   0.10540  -0.0193   1.0000   0.3702
  -7.500  -0.3060   0.10694   0.10095  -0.0181   1.0000   0.3820
  -7.250  -0.3077   0.10447   0.09858  -0.0164   1.0000   0.3885
  -7.000  -0.3121   0.10213   0.09631  -0.0149   1.0000   0.3896
  -6.750  -0.3236   0.10042   0.09472  -0.0130   1.0000   0.3883
  -6.000  -0.4193   0.09324   0.08807  -0.0106   1.0000   0.3032
  -5.750  -0.4680   0.09248   0.08753  -0.0093   1.0000   0.2989
  -5.500  -0.4924   0.05868   0.05260  -0.0645   1.0000   0.1358
  -5.250  -0.4621   0.05292   0.04620  -0.0704   1.0000   0.1172
  -5.000  -0.4246   0.04880   0.04107  -0.0762   1.0000   0.1074
  -4.750  -0.3964   0.04556   0.03743  -0.0786   1.0000   0.1060
  -4.500  -0.3678   0.04285   0.03431  -0.0803   1.0000   0.1041
  -4.250  -0.3404   0.04065   0.03174  -0.0811   1.0000   0.1024
  -4.000  -0.3145   0.03901   0.02975  -0.0815   1.0000   0.1049
  -3.750  -0.2896   0.03779   0.02819  -0.0815   1.0000   0.1101
  -3.500  -0.2722   0.03650   0.02703  -0.0797   1.0000   0.1159
  -3.250  -0.2529   0.03569   0.02618  -0.0781   1.0000   0.1264
  -3.000  -0.2339   0.03496   0.02551  -0.0765   1.0000   0.1399
  -2.750  -0.2068   0.03375   0.02449  -0.0773   1.0000   0.1689
  -2.500  -0.1753   0.03518   0.02808  -0.0762   0.9972   0.5187
  -2.250  -0.1901   0.03929   0.03236  -0.0615   0.9880   0.5825
  -2.000  -0.1958   0.04155   0.03460  -0.0508   0.9798   0.6276
  -1.750  -0.1947   0.04301   0.03593  -0.0427   0.9725   0.6691
  -1.500  -0.1952   0.04355   0.03638  -0.0355   0.9657   0.6998
  -1.250  -0.1925   0.04394   0.03667  -0.0291   0.9600   0.7308
  -1.000  -0.1850   0.04405   0.03664  -0.0249   0.9540   0.7578
  -0.750  -0.1681   0.04405   0.03645  -0.0236   0.9482   0.7738
  -0.500  -0.1380   0.04420   0.03631  -0.0261   0.9424   0.7782
  -0.250  -0.1038   0.04439   0.03624  -0.0303   0.9369   0.7780
   0.000  -0.0625   0.04486   0.03645  -0.0356   0.9310   0.7786
   0.250  -0.0333   0.04508   0.03649  -0.0388   0.9258   0.7790
   0.500   0.0040   0.04560   0.03679  -0.0434   0.9210   0.7798
   0.750   0.0369   0.04612   0.03715  -0.0471   0.9162   0.7816
   1.000   0.0668   0.04664   0.03754  -0.0503   0.9118   0.7839
   1.250   0.1050   0.04742   0.03817  -0.0550   0.9071   0.7866
   1.500   0.1315   0.04801   0.03867  -0.0571   0.9031   0.7890
   1.750   0.1551   0.04862   0.03922  -0.0590   0.8995   0.7921
   2.000   0.1852   0.04945   0.03997  -0.0620   0.8955   0.7961
   2.250   0.2219   0.05050   0.04093  -0.0662   0.8901   0.8007
   2.500   0.2403   0.05123   0.04165  -0.0670   0.8872   0.8045
   2.750   0.2643   0.05214   0.04253  -0.0689   0.8836   0.8090
   3.000   0.3042   0.05339   0.04373  -0.0733   0.8766   0.8151
   3.250   0.3191   0.05426   0.04464  -0.0737   0.8739   0.8203
   3.500   0.3398   0.05538   0.04577  -0.0752   0.8708   0.8262
   3.750   0.3772   0.05663   0.04704  -0.0787   0.8621   0.8334
   4.000   0.3917   0.05778   0.04824  -0.0793   0.8595   0.8397
   4.250   0.4123   0.05903   0.04954  -0.0808   0.8547   0.8473
   4.500   0.4417   0.06031   0.05087  -0.0831   0.8455   0.8568
   4.750   0.4583   0.06157   0.05222  -0.0839   0.8404   0.8657
   5.000   0.4860   0.06283   0.05358  -0.0858   0.8291   0.8768
   5.250   0.5152   0.06399   0.05483  -0.0877   0.8159   0.8903
   5.500   0.5429   0.06503   0.05601  -0.0892   0.8021   0.9074
   5.750   0.5692   0.06601   0.05716  -0.0905   0.7879   0.9330
   6.000   0.5955   0.06730   0.05862  -0.0927   0.7723   1.0000
   6.250   0.6306   0.06903   0.06046  -0.0964   0.7539   1.0000
   6.500   0.6963   0.07026   0.06184  -0.1029   0.7310   1.0000
   6.750   0.7219   0.07203   0.06372  -0.1051   0.7121   1.0000
   7.000   0.7571   0.07357   0.06539  -0.1081   0.6918   1.0000
   7.250   0.8181   0.07404   0.06606  -0.1125   0.6700   1.0000
   7.500   0.8364   0.07589   0.06803  -0.1134   0.6489   1.0000
   7.750   0.8963   0.07550   0.06785  -0.1163   0.6272   1.0000
   8.000   0.9144   0.07708   0.06960  -0.1164   0.6047   1.0000
   8.250   0.9753   0.07534   0.06812  -0.1176   0.5827   1.0000
   8.500   0.9945   0.07628   0.06923  -0.1167   0.5587   1.0000
   8.750   1.0963   0.06834   0.06183  -0.1162   0.5370   1.0000
   9.000   1.1334   0.06572   0.05950  -0.1136   0.5109   1.0000
   9.250   1.3469   0.04046   0.03512  -0.1122   0.4446   1.0000
   9.500   1.3552   0.03917   0.03352  -0.1066   0.3869   1.0000
   9.750   1.3584   0.04001   0.03366  -0.1018   0.3274   1.0000
  10.000   1.3610   0.04239   0.03547  -0.0983   0.2789   1.0000
  10.250   1.3695   0.04508   0.03774  -0.0958   0.2389   1.0000
  10.500   1.3827   0.04784   0.04021  -0.0939   0.2054   1.0000
  10.750   1.4036   0.05077   0.04291  -0.0930   0.1760   1.0000
  11.000   1.4230   0.05402   0.04617  -0.0920   0.1528   1.0000
  11.250   1.4533   0.05775   0.04965  -0.0925   0.1302   1.0000
  11.500   1.4663   0.06147   0.05350  -0.0911   0.1166   1.0000
  11.750   1.4561   0.06477   0.05732  -0.0873   0.1108   1.0000
  12.000   1.4647   0.06891   0.06156  -0.0860   0.1017   1.0000
  12.250   1.4511   0.07282   0.06592  -0.0828   0.0984   1.0000
  12.500   1.4635   0.07723   0.07028  -0.0822   0.0902   1.0000
  12.750   1.4424   0.08151   0.07499  -0.0793   0.0893   1.0000
  13.000   1.4205   0.08628   0.08015  -0.0774   0.0888   1.0000
  13.250   1.3976   0.09151   0.08572  -0.0763   0.0886   1.0000
  13.500   1.3735   0.09719   0.09171  -0.0761   0.0888   1.0000
  13.750   1.3486   0.10336   0.09814  -0.0769   0.0891   1.0000
  14.000   1.3242   0.10999   0.10500  -0.0785   0.0896   1.0000
  14.250   1.3006   0.11711   0.11231  -0.0810   0.0902   1.0000
  14.500   1.2785   0.12469   0.12004  -0.0842   0.0907   1.0000
  14.750   1.0880   0.17775   0.17295  -0.1261   0.1547   1.0000
  15.000   1.0757   0.18890   0.18402  -0.1333   0.1692   1.0000
  15.250   1.0890   0.19558   0.19077  -0.1346   0.1733   1.0000
  15.500   0.8098   0.19970   0.19553  -0.1272   0.2721   1.0000
  15.750   0.8090   0.20230   0.19817  -0.1286   0.2618   1.0000
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