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NREL's S820 Airfoil (s820-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S820 Airfoil (s820-nr)
Reynolds number: 500,000
Max Cl/Cd: 95.06 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s820-nr-500000-n5.txt
Download as CSV file: xf-s820-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S820 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3433   0.06247   0.05918  -0.1082   0.8126   0.0079
  -8.500  -0.4350   0.03577   0.03099  -0.0912   0.7813   0.0045
  -8.250  -0.4306   0.03334   0.02835  -0.0890   0.7784   0.0044
  -8.000  -0.4221   0.03086   0.02562  -0.0870   0.7758   0.0043
  -7.750  -0.4099   0.02848   0.02297  -0.0852   0.7734   0.0042
  -7.500  -0.3944   0.02614   0.02034  -0.0837   0.7712   0.0041
  -7.250  -0.3754   0.02367   0.01758  -0.0825   0.7690   0.0039
  -7.000  -0.3529   0.02148   0.01511  -0.0817   0.7667   0.0038
  -6.750  -0.3282   0.01976   0.01317  -0.0812   0.7646   0.0037
  -6.500  -0.3032   0.01834   0.01157  -0.0808   0.7626   0.0036
  -6.250  -0.2796   0.01712   0.01019  -0.0801   0.7606   0.0036
  -6.000  -0.2580   0.01624   0.00920  -0.0793   0.7586   0.0037
  -5.750  -0.2378   0.01549   0.00836  -0.0782   0.7568   0.0037
  -5.500  -0.2187   0.01477   0.00755  -0.0771   0.7547   0.0038
  -5.250  -0.1987   0.01419   0.00693  -0.0761   0.7524   0.0038
  -5.000  -0.1785   0.01364   0.00632  -0.0751   0.7500   0.0040
  -4.750  -0.1571   0.01317   0.00579  -0.0743   0.7478   0.0041
  -4.500  -0.1348   0.01274   0.00530  -0.0737   0.7459   0.0044
  -4.250  -0.1114   0.01239   0.00487  -0.0732   0.7440   0.0047
  -4.000  -0.0877   0.01203   0.00445  -0.0728   0.7423   0.0053
  -3.750  -0.0626   0.01177   0.00416  -0.0726   0.7406   0.0063
  -3.500  -0.0373   0.01152   0.00389  -0.0725   0.7386   0.0080
  -3.250  -0.0121   0.01126   0.00364  -0.0723   0.7364   0.0155
  -3.000   0.0053   0.01021   0.00319  -0.0714   0.7341   0.1740
  -2.750   0.0123   0.00812   0.00267  -0.0692   0.7318   0.5949
  -2.500   0.0393   0.00826   0.00289  -0.0690   0.7300   0.6412
  -2.250   0.0681   0.00832   0.00285  -0.0694   0.7284   0.6499
  -2.000   0.0972   0.00832   0.00277  -0.0699   0.7269   0.6521
  -1.750   0.1259   0.00831   0.00274  -0.0703   0.7251   0.6540
  -1.500   0.1546   0.00830   0.00270  -0.0707   0.7231   0.6559
  -1.250   0.1834   0.00830   0.00267  -0.0711   0.7209   0.6579
  -1.000   0.2122   0.00830   0.00263  -0.0716   0.7189   0.6599
  -0.750   0.2410   0.00831   0.00260  -0.0720   0.7170   0.6621
  -0.500   0.2700   0.00832   0.00256  -0.0725   0.7153   0.6645
  -0.250   0.2991   0.00834   0.00254  -0.0730   0.7137   0.6666
   0.000   0.3279   0.00836   0.00256  -0.0735   0.7120   0.6684
   0.250   0.3562   0.00837   0.00259  -0.0738   0.7098   0.6703
   0.500   0.3846   0.00838   0.00262  -0.0742   0.7076   0.6723
   0.750   0.4132   0.00841   0.00265  -0.0747   0.7055   0.6745
   1.000   0.4419   0.00843   0.00267  -0.0751   0.7035   0.6768
   1.250   0.4706   0.00846   0.00269  -0.0756   0.7015   0.6792
   1.500   0.4995   0.00849   0.00272  -0.0760   0.6997   0.6815
   1.750   0.5281   0.00852   0.00278  -0.0765   0.6979   0.6836
   2.000   0.5559   0.00855   0.00286  -0.0767   0.6951   0.6857
   2.250   0.5837   0.00856   0.00292  -0.0770   0.6915   0.6880
   2.500   0.6115   0.00855   0.00291  -0.0772   0.6865   0.6904
   2.750   0.6382   0.00853   0.00291  -0.0772   0.6784   0.6929
   3.000   0.6650   0.00851   0.00286  -0.0771   0.6692   0.6953
   3.250   0.6913   0.00850   0.00291  -0.0770   0.6602   0.6974
   3.500   0.7178   0.00852   0.00296  -0.0770   0.6521   0.6997
   3.750   0.7441   0.00855   0.00303  -0.0769   0.6437   0.7023
   4.000   0.7702   0.00860   0.00311  -0.0768   0.6342   0.7051
   4.250   0.7955   0.00866   0.00318  -0.0766   0.6218   0.7080
   4.500   0.8196   0.00876   0.00327  -0.0760   0.6051   0.7107
   4.750   0.8425   0.00889   0.00339  -0.0753   0.5865   0.7130
   5.000   0.8631   0.00908   0.00354  -0.0741   0.5594   0.7156
   5.250   0.8745   0.00953   0.00379  -0.0712   0.5069   0.7186
   5.500   0.8781   0.01024   0.00422  -0.0669   0.4496   0.7218
   5.750   0.8793   0.01091   0.00467  -0.0621   0.4018   0.7250
   6.000   0.8800   0.01161   0.00521  -0.0575   0.3586   0.7280
   6.250   0.8828   0.01240   0.00583  -0.0534   0.3158   0.7315
   6.500   0.8895   0.01313   0.00642  -0.0502   0.2824   0.7354
   6.750   0.8983   0.01383   0.00702  -0.0475   0.2527   0.7391
   7.000   0.9069   0.01458   0.00767  -0.0449   0.2237   0.7424
   7.500   0.9284   0.01601   0.00897  -0.0405   0.1765   0.7499
   7.750   0.9395   0.01678   0.00966  -0.0386   0.1554   0.7539
   8.000   0.9522   0.01749   0.01034  -0.0369   0.1389   0.7576
   8.250   0.9653   0.01820   0.01104  -0.0353   0.1245   0.7619
   8.500   0.9783   0.01895   0.01176  -0.0338   0.1100   0.7667
   8.750   0.9916   0.01970   0.01250  -0.0323   0.0976   0.7714
   9.000   1.0048   0.02045   0.01325  -0.0309   0.0872   0.7763
   9.250   1.0194   0.02117   0.01399  -0.0297   0.0785   0.7817
   9.500   1.0329   0.02195   0.01478  -0.0284   0.0694   0.7869
   9.750   1.0462   0.02276   0.01561  -0.0271   0.0613   0.7930
  10.250   1.0738   0.02434   0.01728  -0.0247   0.0490   0.8068
  10.500   1.0861   0.02526   0.01821  -0.0235   0.0414   0.8146
  10.750   1.0998   0.02606   0.01909  -0.0224   0.0369   0.8233
  11.000   1.1115   0.02701   0.02008  -0.0211   0.0319   0.8329
  11.250   1.1229   0.02799   0.02110  -0.0198   0.0256   0.8451
  11.500   1.1342   0.02895   0.02215  -0.0185   0.0222   0.8610
  11.750   1.1427   0.03003   0.02331  -0.0168   0.0171   0.8847
  12.000   1.1561   0.03119   0.02458  -0.0164   0.0122   0.9477
  12.500   1.1785   0.03358   0.02704  -0.0148   0.0078   1.0000
  12.750   1.1892   0.03488   0.02838  -0.0139   0.0065   1.0000
  13.000   1.1998   0.03620   0.02975  -0.0131   0.0052   1.0000
  13.250   1.2103   0.03756   0.03118  -0.0124   0.0046   1.0000
  13.500   1.2195   0.03906   0.03274  -0.0116   0.0040   1.0000
  13.750   1.2294   0.04053   0.03429  -0.0109   0.0034   1.0000
  14.000   1.2385   0.04210   0.03596  -0.0103   0.0030   1.0000
  14.250   1.2459   0.04386   0.03779  -0.0096   0.0025   1.0000
  14.500   1.2536   0.04563   0.03966  -0.0091   0.0020   1.0000
  14.750   1.2609   0.04750   0.04162  -0.0086   0.0019   1.0000
  15.000   1.2670   0.04950   0.04371  -0.0081   0.0017   1.0000
  15.250   1.2697   0.05193   0.04624  -0.0077   0.0013   1.0000
  15.500   1.2752   0.05410   0.04851  -0.0074   0.0011   1.0000
  15.750   1.2791   0.05651   0.05104  -0.0072   0.0011   1.0000
  16.000   1.2797   0.05938   0.05403  -0.0071   0.0009   1.0000
  16.250   1.2826   0.06203   0.05679  -0.0072   0.0009   1.0000
  16.500   1.2821   0.06514   0.06002  -0.0073   0.0008   1.0000
  16.750   1.2779   0.06888   0.06392  -0.0077   0.0006   1.0000
  17.000   1.2787   0.07208   0.06724  -0.0082   0.0007   1.0000
  17.250   1.2753   0.07594   0.07123  -0.0091   0.0007   1.0000
  17.500   1.2709   0.08006   0.07550  -0.0101   0.0007   1.0000
  17.750   1.2593   0.08545   0.08105  -0.0117   0.0006   1.0000
  18.000   1.2493   0.09082   0.08659  -0.0136   0.0006   1.0000
  18.250   1.2407   0.09618   0.09211  -0.0158   0.0005   1.0000
  18.500   1.2337   0.10134   0.09740  -0.0181   0.0006   1.0000
  18.750   1.2185   0.10826   0.10449  -0.0213   0.0006   1.0000
  19.000   1.2064   0.11478   0.11117  -0.0246   0.0005   1.0000
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