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NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S814 Airfoil (s814-nr)
Reynolds number: 200,000
Max Cl/Cd: 58.29 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s814-nr-200000.txt
Download as CSV file: xf-s814-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S814 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1186   0.10738   0.10210  -0.0371   0.9826   0.3172
  -7.500  -0.0845   0.10509   0.09979  -0.0413   0.9802   0.3189
  -7.250  -0.1278   0.10434   0.09897  -0.0469   0.9700   0.3289
  -7.000  -0.0841   0.10073   0.09535  -0.0506   0.9678   0.3292
  -6.750  -0.0475   0.09770   0.09232  -0.0530   0.9624   0.3297
  -6.500  -0.0111   0.09490   0.08953  -0.0559   0.9571   0.3302
  -6.250   0.0279   0.09226   0.08690  -0.0595   0.9538   0.3309
  -6.000   0.0559   0.09011   0.08477  -0.0610   0.9445   0.3319
  -5.750   0.0899   0.08780   0.08247  -0.0644   0.9391   0.3332
  -5.500   0.0275   0.08884   0.08344  -0.0661   0.9142   0.3442
  -5.250   0.0634   0.08543   0.08005  -0.0676   0.9047   0.3446
  -5.000   0.1004   0.08241   0.07703  -0.0694   0.8931   0.3449
  -4.750   0.1408   0.07949   0.07411  -0.0723   0.8797   0.3454
  -4.500   0.1921   0.07637   0.07095  -0.0778   0.8671   0.3460
  -4.250   0.2588   0.07292   0.06742  -0.0874   0.8530   0.3469
  -4.000   0.3359   0.06940   0.06375  -0.1000   0.8313   0.3484
  -3.750   0.3943   0.06696   0.06105  -0.1087   0.7974   0.3504
  -3.500   0.3382   0.06815   0.06196  -0.1090   0.7661   0.3603
  -3.250   0.3703   0.06609   0.05973  -0.1098   0.7424   0.3607
  -3.000   0.3977   0.06452   0.05802  -0.1099   0.7221   0.3611
  -2.750   0.4231   0.06318   0.05657  -0.1096   0.7046   0.3616
  -2.500   0.4464   0.06202   0.05531  -0.1092   0.6891   0.3622
  -2.250   0.4676   0.06102   0.05426  -0.1086   0.6749   0.3629
  -2.000   0.4878   0.06012   0.05332  -0.1081   0.6631   0.3639
  -1.750   0.5082   0.05933   0.05242  -0.1077   0.6531   0.3653
  -1.500   0.4244   0.06090   0.05404  -0.1027   0.6466   0.3765
  -1.250   0.4550   0.05899   0.05207  -0.1031   0.6380   0.3768
  -1.000   0.4837   0.05748   0.05055  -0.1032   0.6297   0.3772
  -0.750   0.5096   0.05623   0.04928  -0.1030   0.6223   0.3776
  -0.500   0.5364   0.05516   0.04818  -0.1031   0.6158   0.3782
  -0.250   0.5591   0.05422   0.04728  -0.1026   0.6089   0.3789
   0.000   0.5817   0.05337   0.04639  -0.1023   0.6031   0.3798
   0.250   0.6022   0.05263   0.04567  -0.1018   0.5974   0.3810
   0.500   0.6193   0.05193   0.04502  -0.1010   0.5919   0.3824
   0.750   0.6355   0.05125   0.04434  -0.1004   0.5873   0.3845
   1.000   0.6457   0.05065   0.04370  -0.0998   0.5836   0.3885
   1.250   0.5953   0.04969   0.04283  -0.0944   0.5806   0.3944
   1.500   0.6180   0.04887   0.04208  -0.0936   0.5761   0.3951
   1.750   0.6406   0.04809   0.04134  -0.0931   0.5721   0.3958
   2.000   0.6648   0.04739   0.04063  -0.0929   0.5684   0.3969
   2.250   0.6836   0.04681   0.04007  -0.0923   0.5648   0.3981
   2.500   0.6949   0.04632   0.03969  -0.0905   0.5610   0.3999
   2.750   0.7050   0.04576   0.03920  -0.0891   0.5575   0.4024
   3.000   0.6962   0.02374   0.01587  -0.1299   0.5555   0.3771
   3.250   0.7254   0.02364   0.01582  -0.1304   0.5524   0.3784
   3.500   0.7565   0.02374   0.01594  -0.1311   0.5494   0.3798
   3.750   0.7817   0.02385   0.01617  -0.1308   0.5458   0.3814
   4.000   0.8070   0.02395   0.01640  -0.1305   0.5421   0.3831
   4.250   0.8353   0.02397   0.01647  -0.1309   0.5384   0.3853
   4.500   0.8678   0.02384   0.01631  -0.1322   0.5347   0.3882
   4.750   0.9059   0.02372   0.01603  -0.1349   0.5313   0.3913
   5.000   0.9316   0.02358   0.01596  -0.1351   0.5272   0.3936
   5.250   0.9565   0.02358   0.01611  -0.1347   0.5229   0.3953
   5.500   0.9845   0.02364   0.01625  -0.1347   0.5187   0.3971
   5.750   1.0177   0.02375   0.01633  -0.1357   0.5145   0.3994
   6.000   1.0389   0.02383   0.01658  -0.1346   0.5092   0.4016
   6.250   1.0649   0.02378   0.01658  -0.1344   0.5032   0.4045
   6.500   1.1009   0.02366   0.01630  -0.1360   0.4976   0.4080
   6.750   1.1224   0.02362   0.01638  -0.1350   0.4910   0.4107
   7.000   1.1465   0.02352   0.01639  -0.1342   0.4842   0.4130
   7.250   1.1749   0.02355   0.01644  -0.1341   0.4780   0.4158
   7.500   1.1930   0.02358   0.01663  -0.1323   0.4709   0.4188
   7.750   1.2226   0.02347   0.01647  -0.1325   0.4642   0.4226
   8.000   1.2437   0.02350   0.01655  -0.1314   0.4569   0.4260
   8.250   1.2660   0.02330   0.01643  -0.1303   0.4489   0.4287
   8.500   1.2850   0.02329   0.01653  -0.1286   0.4411   0.4313
   8.750   1.3020   0.02323   0.01656  -0.1265   0.4323   0.4341
   9.000   1.3188   0.02323   0.01663  -0.1245   0.4235   0.4375
   9.250   1.3336   0.02318   0.01661  -0.1221   0.4140   0.4411
   9.500   1.3429   0.02321   0.01672  -0.1188   0.4042   0.4441
   9.750   1.3540   0.02323   0.01678  -0.1158   0.3940   0.4468
  10.000   1.3592   0.02350   0.01724  -0.1121   0.3812   0.4496
  10.250   1.3662   0.02384   0.01768  -0.1088   0.3665   0.4530
  10.500   1.3719   0.02430   0.01816  -0.1054   0.3480   0.4567
  10.750   1.3747   0.02501   0.01881  -0.1020   0.3233   0.4601
  11.000   1.3699   0.02612   0.01980  -0.0978   0.2938   0.4625
  11.250   1.3593   0.02780   0.02135  -0.0935   0.2660   0.4645
  11.500   1.3487   0.02982   0.02328  -0.0897   0.2401   0.4666
  11.750   1.3362   0.03226   0.02562  -0.0864   0.2177   0.4688
  12.000   1.3258   0.03488   0.02818  -0.0838   0.1969   0.4713
  12.250   1.3150   0.03782   0.03105  -0.0818   0.1784   0.4738
  12.500   1.3048   0.04103   0.03418  -0.0803   0.1623   0.4764
  12.750   1.2950   0.04442   0.03754  -0.0793   0.1482   0.4787
  13.000   1.2854   0.04797   0.04110  -0.0786   0.1362   0.4807
  13.250   1.2752   0.05177   0.04488  -0.0781   0.1257   0.4829
  13.500   1.2703   0.05520   0.04836  -0.0779   0.1156   0.4857
  13.750   1.2641   0.05891   0.05207  -0.0779   0.1073   0.4888
  14.000   1.2585   0.06267   0.05581  -0.0781   0.0998   0.4921
  14.250   1.2566   0.06616   0.05931  -0.0784   0.0929   0.4955
  14.500   1.2530   0.06981   0.06299  -0.0788   0.0870   0.4983
  14.750   1.2524   0.07318   0.06642  -0.0792   0.0815   0.5016
  15.000   1.2531   0.07653   0.06981  -0.0797   0.0766   0.5055
  15.250   1.2525   0.07997   0.07320  -0.0801   0.0724   0.5095
  15.500   1.2572   0.08299   0.07633  -0.0807   0.0683   0.5136
  15.750   1.2594   0.08622   0.07962  -0.0814   0.0649   0.5175
  16.000   1.2635   0.08908   0.08245  -0.0817   0.0615   0.5223
  16.250   1.2686   0.09211   0.08558  -0.0824   0.0586   0.5279
  16.500   1.2735   0.09512   0.08867  -0.0832   0.0560   0.5327
  16.750   1.2811   0.09743   0.09091  -0.0834   0.0533   0.5384
  17.000   1.2873   0.10037   0.09398  -0.0841   0.0513   0.5448
  17.250   1.2929   0.10335   0.09710  -0.0850   0.0492   0.5502
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