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NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S831 Airfoil (s831-nr)
Reynolds number: 200,000
Max Cl/Cd: 46.96 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s831-nr-200000-n5.txt
Download as CSV file: xf-s831-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S831 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0919   0.09274   0.08800  -0.1668   0.8333   0.0219
 -11.000   0.0953   0.08975   0.08501  -0.1679   0.8286   0.0223
 -10.750   0.0989   0.08675   0.08199  -0.1691   0.8245   0.0226
 -10.500   0.1017   0.08355   0.07875  -0.1706   0.8210   0.0228
 -10.250   0.1027   0.08042   0.07565  -0.1717   0.8167   0.0230
 -10.000   0.1035   0.07716   0.07240  -0.1731   0.8127   0.0232
  -9.750   0.1025   0.07346   0.06869  -0.1748   0.8091   0.0231
  -9.500   0.1003   0.06962   0.06483  -0.1770   0.8056   0.0229
  -9.250   0.0927   0.06535   0.06059  -0.1795   0.8011   0.0229
  -9.000   0.0813   0.06144   0.05664  -0.1813   0.7968   0.0226
  -8.750   0.0682   0.05799   0.05310  -0.1821   0.7932   0.0224
  -8.500   0.0341   0.05273   0.04765  -0.1800   0.7880   0.0148
  -8.250   0.0232   0.05106   0.04594  -0.1777   0.7841   0.0145
  -8.000   0.0191   0.04949   0.04428  -0.1764   0.7810   0.0165
  -7.500   0.0058   0.04182   0.03603  -0.1707   0.7749   0.0112
  -7.250   0.0090   0.03982   0.03388  -0.1688   0.7718   0.0111
  -7.000   0.0158   0.03776   0.03165  -0.1672   0.7689   0.0109
  -6.750   0.0256   0.03550   0.02914  -0.1657   0.7665   0.0107
  -6.500   0.0389   0.03314   0.02649  -0.1645   0.7644   0.0105
  -6.250   0.0518   0.03096   0.02405  -0.1628   0.7618   0.0103
  -6.000   0.0654   0.02880   0.02161  -0.1609   0.7591   0.0101
  -5.750   0.0826   0.02666   0.01916  -0.1594   0.7567   0.0100
  -5.500   0.1032   0.02467   0.01685  -0.1582   0.7546   0.0099
  -5.250   0.1264   0.02290   0.01477  -0.1573   0.7529   0.0100
  -5.000   0.1510   0.02145   0.01307  -0.1567   0.7513   0.0103
  -4.750   0.1756   0.02032   0.01175  -0.1561   0.7499   0.0107
  -4.500   0.1955   0.01956   0.01087  -0.1549   0.7480   0.0111
  -4.250   0.2111   0.01900   0.01030  -0.1530   0.7453   0.0118
  -4.000   0.2297   0.01857   0.00985  -0.1518   0.7429   0.0126
  -3.750   0.2509   0.01819   0.00942  -0.1511   0.7408   0.0159
  -3.500   0.2743   0.01786   0.00905  -0.1509   0.7390   0.0195
  -3.250   0.2989   0.01746   0.00862  -0.1509   0.7375   0.0263
  -3.000   0.3249   0.01706   0.00821  -0.1514   0.7361   0.0369
  -2.750   0.3527   0.01670   0.00779  -0.1521   0.7350   0.0499
  -2.500   0.3718   0.01654   0.00764  -0.1511   0.7328   0.0643
  -2.250   0.3917   0.01628   0.00752  -0.1504   0.7305   0.1045
  -2.000   0.4105   0.01484   0.00778  -0.1507   0.7285   0.6207
  -1.750   0.4342   0.01516   0.00807  -0.1499   0.7265   0.6532
  -1.500   0.4592   0.01547   0.00832  -0.1493   0.7249   0.6728
  -1.250   0.4851   0.01576   0.00855  -0.1488   0.7234   0.6874
  -1.000   0.5117   0.01604   0.00876  -0.1486   0.7222   0.6996
  -0.750   0.5406   0.01619   0.00882  -0.1490   0.7212   0.7064
  -0.500   0.5699   0.01624   0.00876  -0.1500   0.7200   0.7091
  -0.250   0.5841   0.01652   0.00904  -0.1479   0.7174   0.7114
   0.000   0.6018   0.01677   0.00929  -0.1465   0.7151   0.7132
   0.250   0.6229   0.01696   0.00947  -0.1457   0.7131   0.7152
   0.500   0.6473   0.01709   0.00956  -0.1455   0.7114   0.7173
   0.750   0.6741   0.01719   0.00961  -0.1459   0.7099   0.7195
   1.000   0.7027   0.01727   0.00965  -0.1466   0.7086   0.7219
   1.250   0.7329   0.01735   0.00967  -0.1477   0.7076   0.7244
   1.500   0.7636   0.01743   0.00972  -0.1488   0.7067   0.7266
   1.750   0.7919   0.01757   0.00985  -0.1494   0.7058   0.7285
   2.000   0.7743   0.01848   0.01091  -0.1413   0.7008   0.7314
   2.250   0.7863   0.01888   0.01134  -0.1389   0.6980   0.7342
   2.500   0.8089   0.01912   0.01158  -0.1385   0.6963   0.7369
   2.750   0.8351   0.01931   0.01177  -0.1389   0.6950   0.7397
   3.000   0.8630   0.01946   0.01193  -0.1395   0.6939   0.7421
   3.250   0.8919   0.01959   0.01210  -0.1402   0.6930   0.7440
   3.500   0.9232   0.01966   0.01220  -0.1414   0.6922   0.7463
   4.500   0.9013   0.02480   0.01764  -0.1217   0.6734   0.7597
   4.750   0.9523   0.02390   0.01679  -0.1257   0.6753   0.7619
   5.000   1.0025   0.02316   0.01609  -0.1298   0.6766   0.7644
   6.500   1.0274   0.03021   0.02362  -0.1124   0.6476   0.7859
   7.000   1.0403   0.03253   0.02615  -0.1078   0.6354   0.7924
   7.250   1.0757   0.03181   0.02553  -0.1090   0.6348   0.7963
   7.500   1.1161   0.03068   0.02450  -0.1107   0.6341   0.8006
   8.000   1.1443   0.03110   0.02513  -0.1073   0.6194   0.8084
   8.250   1.1368   0.03296   0.02708  -0.1034   0.6074   0.8130
   8.750   1.1708   0.03324   0.02758  -0.1010   0.5909   0.8217
   9.750   1.1878   0.03897   0.03375  -0.0924   0.5375   0.8431
  10.000   1.2121   0.03866   0.03352  -0.0921   0.5214   0.8488
  10.250   1.2631   0.03577   0.03060  -0.0937   0.4882   0.8557
  10.500   1.2962   0.03406   0.02834  -0.0931   0.4144   0.8627
  10.750   1.2864   0.03639   0.03038  -0.0893   0.3653   0.8707
  11.000   1.2741   0.03916   0.03292  -0.0856   0.3221   0.8799
  11.250   1.2637   0.04195   0.03552  -0.0824   0.2831   0.8914
  11.500   1.2551   0.04461   0.03804  -0.0795   0.2471   0.9097
  11.750   1.2476   0.04690   0.04023  -0.0767   0.2160   1.0000
  12.000   1.2458   0.04953   0.04271  -0.0751   0.1843   1.0000
  12.250   1.2463   0.05204   0.04508  -0.0738   0.1567   1.0000
  12.500   1.2489   0.05440   0.04733  -0.0727   0.1329   1.0000
  12.750   1.2528   0.05667   0.04952  -0.0717   0.1123   1.0000
  13.000   1.2574   0.05892   0.05168  -0.0709   0.0943   1.0000
  13.500   1.2686   0.06327   0.05596  -0.0694   0.0677   1.0000
  13.750   1.2751   0.06543   0.05811  -0.0688   0.0568   1.0000
  14.000   1.2819   0.06758   0.06030  -0.0683   0.0477   1.0000
  14.250   1.2882   0.06979   0.06254  -0.0678   0.0398   1.0000
  14.500   1.2935   0.07215   0.06492  -0.0673   0.0331   1.0000
  14.750   1.2977   0.07466   0.06744  -0.0668   0.0276   1.0000
  15.000   1.3035   0.07703   0.06988  -0.0664   0.0230   1.0000
  15.250   1.3076   0.07964   0.07256  -0.0661   0.0193   1.0000
  15.500   1.3115   0.08228   0.07524  -0.0658   0.0162   1.0000
  15.750   1.3154   0.08499   0.07806  -0.0656   0.0138   1.0000
  16.000   1.3183   0.08781   0.08094  -0.0654   0.0119   1.0000
  16.250   1.3212   0.09070   0.08398  -0.0654   0.0101   1.0000
  16.500   1.3236   0.09369   0.08708  -0.0654   0.0089   1.0000
  16.750   1.3229   0.09715   0.09065  -0.0655   0.0080   1.0000
  17.000   1.3242   0.10039   0.09405  -0.0657   0.0071   1.0000
  17.250   1.3248   0.10372   0.09750  -0.0661   0.0065   1.0000
  17.500   1.3226   0.10750   0.10137  -0.0666   0.0059   1.0000
  17.750   1.3240   0.11081   0.10487  -0.0672   0.0052   1.0000
  18.000   1.3245   0.11428   0.10848  -0.0680   0.0047   1.0000
  18.250   1.3232   0.11806   0.11238  -0.0690   0.0043   1.0000
  18.500   1.3185   0.12244   0.11690  -0.0702   0.0041   1.0000
  18.750   1.3159   0.12654   0.12115  -0.0715   0.0040   1.0000
  19.000   1.3127   0.13080   0.12560  -0.0730   0.0037   1.0000
  19.250   1.3090   0.13517   0.13014  -0.0746   0.0036   1.0000
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