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NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S828 Airfoil (s828-nr)
Reynolds number: 500,000
Max Cl/Cd: 76.86 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s828-nr-500000.txt
Download as CSV file: xf-s828-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S828 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2666   0.08961   0.08666  -0.1041   0.8412   0.0159
 -11.500  -0.2725   0.08439   0.08144  -0.1067   0.8379   0.0158
  -8.250  -0.4683   0.02731   0.02163  -0.0794   0.8008   0.0082
  -8.000  -0.4531   0.02386   0.01775  -0.0775   0.7992   0.0075
  -7.750  -0.4171   0.02046   0.01386  -0.0792   0.7980   0.0071
  -7.500  -0.3841   0.01890   0.01209  -0.0805   0.7968   0.0071
  -7.250  -0.3567   0.01781   0.01086  -0.0808   0.7954   0.0072
  -7.000  -0.3330   0.01701   0.00996  -0.0804   0.7939   0.0078
  -6.750  -0.3100   0.01645   0.00931  -0.0798   0.7925   0.0088
  -6.500  -0.2920   0.01543   0.00820  -0.0783   0.7913   0.0096
  -6.250  -0.2722   0.01491   0.00761  -0.0773   0.7900   0.0103
  -6.000  -0.2510   0.01454   0.00721  -0.0764   0.7889   0.0123
  -5.750  -0.2314   0.01405   0.00672  -0.0753   0.7876   0.0151
  -5.500  -0.2125   0.01353   0.00620  -0.0739   0.7863   0.0222
  -5.250  -0.1953   0.01297   0.00577  -0.0723   0.7850   0.0491
  -5.000  -0.1776   0.01255   0.00554  -0.0708   0.7837   0.0859
  -4.750  -0.1620   0.01210   0.00532  -0.0690   0.7824   0.1386
  -4.500  -0.1514   0.01153   0.00512  -0.0663   0.7812   0.2227
  -4.250  -0.1491   0.01092   0.00494  -0.0618   0.7798   0.3296
  -4.000  -0.1571   0.01021   0.00475  -0.0552   0.7783   0.4578
  -3.750  -0.1693   0.00938   0.00453  -0.0474   0.7767   0.6027
  -3.500  -0.1577   0.00929   0.00513  -0.0435   0.7757   0.7705
  -3.250  -0.1365   0.00962   0.00542  -0.0420   0.7748   0.8008
  -3.000  -0.1150   0.00998   0.00573  -0.0406   0.7738   0.8182
  -2.750  -0.0829   0.01053   0.00625  -0.0412   0.7730   0.8269
  -2.500  -0.0555   0.01093   0.00660  -0.0411   0.7721   0.8344
  -2.250  -0.0203   0.01153   0.00717  -0.0423   0.7713   0.8398
  -2.000   0.0048   0.01190   0.00748  -0.0417   0.7703   0.8472
  -1.750   0.0483   0.01262   0.00817  -0.0445   0.7698   0.8498
  -1.500   0.0806   0.01341   0.00894  -0.0449   0.7690   0.8601
  -1.250   0.1503   0.01442   0.00989  -0.0526   0.7689   0.8614
  -1.000   0.1955   0.01466   0.01010  -0.0563   0.7683   0.8621
  -0.750   0.2342   0.01477   0.01018  -0.0589   0.7676   0.8630
  -0.500   0.2694   0.01486   0.01025  -0.0608   0.7669   0.8642
  -0.250   0.3015   0.01494   0.01032  -0.0621   0.7662   0.8657
   0.000   0.3262   0.01501   0.01037  -0.0619   0.7654   0.8687
   0.250   0.3230   0.01497   0.01033  -0.0560   0.7642   0.8757
   0.500   0.3579   0.01501   0.01036  -0.0579   0.7635   0.8764
   0.750   0.3912   0.01505   0.01040  -0.0595   0.7628   0.8772
   1.000   0.4228   0.01512   0.01048  -0.0607   0.7621   0.8783
   1.250   0.4518   0.01523   0.01059  -0.0615   0.7614   0.8796
   1.500   0.4651   0.01538   0.01079  -0.0591   0.7598   0.8830
   1.750   0.4453   0.01542   0.01089  -0.0498   0.7567   0.8901
   2.000   0.4726   0.01549   0.01100  -0.0502   0.7551   0.8910
   2.250   0.5005   0.01555   0.01109  -0.0508   0.7538   0.8921
   2.500   0.5255   0.01559   0.01116  -0.0507   0.7524   0.8934
   2.750   0.5477   0.01558   0.01117  -0.0500   0.7511   0.8951
   3.000   0.5606   0.01549   0.01110  -0.0473   0.7496   0.8984
   3.250   0.5620   0.01523   0.01083  -0.0424   0.7479   0.9030
   3.500   0.5752   0.01535   0.01103  -0.0399   0.7433   0.9043
   3.750   0.6083   0.01487   0.01057  -0.0410   0.7389   0.9048
   4.000   0.6591   0.01397   0.00960  -0.0454   0.7341   0.9044
   4.250   0.6777   0.01374   0.00943  -0.0437   0.7273   0.9057
   4.500   0.7122   0.01329   0.00898  -0.0450   0.7222   0.9063
   4.750   0.7392   0.01301   0.00874  -0.0450   0.7167   0.9073
   5.000   0.7565   0.01276   0.00855  -0.0431   0.7109   0.9091
   5.250   0.7894   0.01237   0.00815  -0.0442   0.7053   0.9098
   5.500   0.7891   0.01218   0.00806  -0.0389   0.6996   0.9134
   5.750   0.8107   0.01176   0.00763  -0.0378   0.6919   0.9157
   6.000   0.8178   0.01150   0.00747  -0.0337   0.6828   0.9175
   6.250   0.8311   0.01125   0.00730  -0.0309   0.6728   0.9191
   6.500   0.8366   0.01103   0.00714  -0.0264   0.6592   0.9213
   6.750   0.8297   0.01081   0.00697  -0.0194   0.6426   0.9250
   7.000   0.8247   0.01073   0.00683  -0.0132   0.6075   0.9287
   7.250   0.8039   0.01117   0.00693  -0.0041   0.5438   0.9324
   7.500   0.7792   0.01221   0.00767   0.0049   0.4857   0.9367
   7.750   0.7611   0.01342   0.00864   0.0120   0.4334   0.9413
   8.000   0.7469   0.01476   0.00973   0.0179   0.3807   0.9446
   8.250   0.7374   0.01603   0.01078   0.0230   0.3289   0.9479
   8.500   0.7329   0.01726   0.01178   0.0271   0.2788   0.9511
   8.750   0.7316   0.01846   0.01273   0.0305   0.2281   0.9543
   9.000   0.7325   0.01960   0.01362   0.0335   0.1784   0.9575
   9.250   0.7397   0.02057   0.01443   0.0356   0.1408   0.9602
   9.500   0.7493   0.02151   0.01522   0.0372   0.1077   0.9627
   9.750   0.7602   0.02242   0.01601   0.0386   0.0816   0.9654
  10.000   0.7714   0.02337   0.01685   0.0399   0.0601   0.9682
  10.250   0.7849   0.02427   0.01769   0.0408   0.0459   0.9708
  10.500   0.8015   0.02527   0.01869   0.0410   0.0370   0.9728
  10.750   0.8166   0.02643   0.01983   0.0412   0.0301   0.9749
  11.000   0.8364   0.02729   0.02080   0.0409   0.0274   0.9769
  11.250   0.8554   0.02824   0.02176   0.0406   0.0234   0.9790
  11.500   0.8713   0.02945   0.02303   0.0405   0.0202   0.9814
  11.750   0.8944   0.03019   0.02379   0.0396   0.0171   0.9835
  12.000   0.9106   0.03152   0.02516   0.0392   0.0141   0.9853
  12.250   0.9310   0.03253   0.02624   0.0385   0.0124   0.9873
  12.500   0.9457   0.03396   0.02768   0.0382   0.0099   0.9897
  12.750   0.9654   0.03494   0.02877   0.0376   0.0083   0.9927
  13.250   0.9860   0.03778   0.03173   0.0388   0.0054   1.0000
  13.500   0.9921   0.03913   0.03316   0.0402   0.0051   1.0000
  13.750   0.9959   0.04088   0.03495   0.0415   0.0044   1.0000
  14.000   1.0013   0.04261   0.03680   0.0426   0.0040   1.0000
  14.250   1.0054   0.04454   0.03883   0.0436   0.0041   1.0000
  14.500   1.0108   0.04647   0.04090   0.0445   0.0038   1.0000
  14.750   1.0175   0.04831   0.04286   0.0450   0.0035   1.0000
  15.000   1.0214   0.05048   0.04515   0.0457   0.0032   1.0000
  15.250   1.0224   0.05300   0.04782   0.0465   0.0033   1.0000
  15.500   1.0269   0.05520   0.05008   0.0465   0.0028   1.0000
  15.750   1.0288   0.05777   0.05282   0.0469   0.0029   1.0000
  16.000   1.0260   0.06095   0.05619   0.0473   0.0030   1.0000
  16.250   1.0244   0.06406   0.05940   0.0472   0.0028   1.0000
  16.500   1.0195   0.06773   0.06324   0.0470   0.0028   1.0000
  16.750   1.0085   0.07232   0.06800   0.0466   0.0027   1.0000
  17.000   1.0038   0.07630   0.07215   0.0458   0.0027   1.0000
  17.250   0.9839   0.08259   0.07866   0.0444   0.0026   1.0000
  17.500   0.9824   0.08647   0.08266   0.0429   0.0027   1.0000
  17.750   0.9689   0.09244   0.08883   0.0408   0.0027   1.0000
  18.000   0.9342   0.10233   0.09899   0.0368   0.0026   1.0000
  18.250   0.9354   0.10636   0.10313   0.0345   0.0027   1.0000
  18.500   0.9173   0.11415   0.11109   0.0305   0.0026   1.0000
  18.750   0.9024   0.12180   0.11891   0.0263   0.0027   1.0000
  19.000   0.8848   0.13035   0.12765   0.0215   0.0028   1.0000
  19.250   0.8550   0.14246   0.14001   0.0149   0.0029   1.0000
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