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NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S818 Airfoil (s818-nr)
Reynolds number: 500,000
Max Cl/Cd: 83.4 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s818-nr-500000.txt
Download as CSV file: xf-s818-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S818 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.7238   0.09180   0.08736  -0.0394   1.0000   0.0888
 -14.250  -0.7264   0.08918   0.08484  -0.0393   1.0000   0.1004
 -14.000  -0.7386   0.08548   0.08129  -0.0394   1.0000   0.1177
 -13.750  -0.7608   0.08076   0.07677  -0.0396   1.0000   0.1433
 -13.500  -0.7962   0.07482   0.07105  -0.0397   1.0000   0.1737
 -13.250  -0.8390   0.06851   0.06499  -0.0397   1.0000   0.2027
 -12.000  -1.0206   0.03910   0.03572  -0.0454   0.9923   0.2883
 -11.750  -1.0705   0.03033   0.02668  -0.0521   0.9811   0.2855
 -11.500  -0.9052   0.04288   0.03952  -0.0500   0.9882   0.3116
 -11.250  -0.9109   0.03798   0.03453  -0.0555   0.9828   0.3161
 -11.000  -0.8448   0.04074   0.03726  -0.0583   0.9822   0.3214
 -10.750  -0.8166   0.04007   0.03654  -0.0607   0.9788   0.3240
 -10.500  -0.8431   0.03372   0.03009  -0.0653   0.9696   0.3268
 -10.250  -0.8425   0.03158   0.02789  -0.0662   0.9607   0.3290
 -10.000  -0.8171   0.02970   0.02592  -0.0714   0.9560   0.3325
  -9.750  -0.7667   0.03048   0.02665  -0.0752   0.9549   0.3358
  -9.500  -0.7129   0.03210   0.02827  -0.0772   0.9544   0.3382
  -6.750  -0.4177   0.02521   0.02101  -0.0890   0.8846   0.3494
  -6.500  -0.3967   0.02022   0.01559  -0.0972   0.8724   0.3510
  -6.250  -0.3490   0.01892   0.01414  -0.1028   0.8647   0.3514
  -6.000  -0.2981   0.01795   0.01301  -0.1087   0.8510   0.3517
  -5.750  -0.2354   0.01720   0.01207  -0.1167   0.8336   0.3520
  -5.500  -0.1830   0.01671   0.01136  -0.1226   0.8071   0.3522
  -5.250  -0.1493   0.01640   0.01082  -0.1245   0.7766   0.3525
  -5.000  -0.1245   0.01581   0.01000  -0.1250   0.7479   0.3531
  -4.750  -0.1014   0.01535   0.00937  -0.1248   0.7223   0.3537
  -4.500  -0.0782   0.01506   0.00893  -0.1244   0.6992   0.3541
  -4.250  -0.0547   0.01485   0.00859  -0.1240   0.6786   0.3546
  -4.000  -0.0306   0.01468   0.00831  -0.1237   0.6596   0.3550
  -3.750  -0.0061   0.01453   0.00806  -0.1234   0.6419   0.3555
  -3.500   0.0187   0.01442   0.00784  -0.1232   0.6255   0.3559
  -3.250   0.0441   0.01431   0.00764  -0.1231   0.6100   0.3564
  -3.000   0.0701   0.01421   0.00747  -0.1230   0.5957   0.3568
  -2.750   0.0963   0.01414   0.00732  -0.1230   0.5826   0.3574
  -2.500   0.1225   0.01409   0.00720  -0.1230   0.5704   0.3580
  -2.250   0.1490   0.01406   0.00710  -0.1230   0.5588   0.3586
  -2.000   0.1763   0.01401   0.00699  -0.1231   0.5483   0.3593
  -1.750   0.2032   0.01398   0.00689  -0.1232   0.5384   0.3600
  -1.500   0.2310   0.01390   0.00677  -0.1235   0.5289   0.3607
  -1.250   0.2586   0.01388   0.00666  -0.1237   0.5205   0.3613
  -1.000   0.2868   0.01381   0.00656  -0.1241   0.5126   0.3621
  -0.750   0.3147   0.01381   0.00648  -0.1244   0.5055   0.3628
  -0.500   0.3435   0.01375   0.00640  -0.1248   0.4992   0.3636
  -0.250   0.3719   0.01372   0.00632  -0.1252   0.4930   0.3644
   0.000   0.4006   0.01376   0.00628  -0.1256   0.4874   0.3652
   0.250   0.4295   0.01371   0.00623  -0.1260   0.4825   0.3659
   0.500   0.4582   0.01371   0.00620  -0.1264   0.4776   0.3666
   0.750   0.4871   0.01377   0.00620  -0.1268   0.4731   0.3673
   1.000   0.5166   0.01383   0.00622  -0.1273   0.4691   0.3678
   1.250   0.5459   0.01372   0.00612  -0.1279   0.4654   0.3688
   1.500   0.5751   0.01361   0.00602  -0.1284   0.4616   0.3702
   1.750   0.6038   0.01362   0.00603  -0.1288   0.4580   0.3713
   2.000   0.6338   0.01374   0.00612  -0.1294   0.4543   0.3724
   2.250   0.6628   0.01377   0.00620  -0.1298   0.4516   0.3734
   2.500   0.6914   0.01381   0.00628  -0.1301   0.4489   0.3745
   2.750   0.7203   0.01386   0.00636  -0.1304   0.4462   0.3756
   3.000   0.7493   0.01393   0.00645  -0.1308   0.4437   0.3768
   3.250   0.7788   0.01403   0.00654  -0.1312   0.4412   0.3781
   3.500   0.8095   0.01417   0.00667  -0.1320   0.4387   0.3794
   3.750   0.8416   0.01436   0.00684  -0.1330   0.4363   0.3808
   4.000   0.8702   0.01443   0.00695  -0.1333   0.4346   0.3820
   4.250   0.8991   0.01452   0.00708  -0.1336   0.4327   0.3831
   4.500   0.9279   0.01463   0.00721  -0.1339   0.4306   0.3840
   4.750   0.9573   0.01461   0.00725  -0.1344   0.4284   0.3861
   5.000   0.9866   0.01468   0.00738  -0.1349   0.4264   0.3878
   5.250   1.0160   0.01482   0.00756  -0.1353   0.4247   0.3894
   5.500   1.0462   0.01500   0.00777  -0.1359   0.4229   0.3912
   5.750   1.0785   0.01525   0.00804  -0.1369   0.4209   0.3931
   6.000   1.1100   0.01549   0.00832  -0.1378   0.4192   0.3951
   6.250   1.1368   0.01560   0.00850  -0.1377   0.4176   0.3969
   6.500   1.1628   0.01570   0.00867  -0.1375   0.4153   0.3985
   6.750   1.1875   0.01578   0.00880  -0.1369   0.4120   0.3998
   7.000   1.2073   0.01573   0.00875  -0.1355   0.4064   0.4017
   7.250   1.2266   0.01576   0.00884  -0.1340   0.4002   0.4038
   7.500   1.2450   0.01577   0.00895  -0.1322   0.3956   0.4057
   7.750   1.2680   0.01588   0.00912  -0.1314   0.3921   0.4077
   8.000   1.2923   0.01608   0.00932  -0.1309   0.3881   0.4098
   8.250   1.3147   0.01625   0.00956  -0.1300   0.3840   0.4119
   8.500   1.3351   0.01637   0.00977  -0.1287   0.3799   0.4140
   8.750   1.3565   0.01652   0.00997  -0.1277   0.3758   0.4158
   9.000   1.3783   0.01672   0.01018  -0.1268   0.3710   0.4181
   9.250   1.3990   0.01687   0.01045  -0.1256   0.3663   0.4208
   9.500   1.4187   0.01701   0.01071  -0.1243   0.3606   0.4232
   9.750   1.4373   0.01728   0.01100  -0.1229   0.3545   0.4258
  10.000   1.4570   0.01750   0.01132  -0.1216   0.3481   0.4287
  10.250   1.4750   0.01777   0.01164  -0.1201   0.3400   0.4313
  10.500   1.4937   0.01807   0.01199  -0.1188   0.3311   0.4338
  10.750   1.5096   0.01844   0.01242  -0.1171   0.3186   0.4371
  11.000   1.5235   0.01896   0.01295  -0.1152   0.2984   0.4399
  11.250   1.5245   0.02009   0.01392  -0.1116   0.2633   0.4423
  11.500   1.5153   0.02193   0.01554  -0.1070   0.2275   0.4443
  11.750   1.5069   0.02391   0.01737  -0.1029   0.1983   0.4464
  12.000   1.4997   0.02598   0.01933  -0.0993   0.1735   0.4484
  12.250   1.4914   0.02828   0.02153  -0.0961   0.1534   0.4501
  12.500   1.4849   0.03067   0.02390  -0.0935   0.1365   0.4528
  12.750   1.4783   0.03327   0.02650  -0.0914   0.1226   0.4552
  13.000   1.4718   0.03610   0.02933  -0.0897   0.1108   0.4577
  13.250   1.4665   0.03902   0.03230  -0.0884   0.1012   0.4603
  13.500   1.4599   0.04227   0.03557  -0.0874   0.0933   0.4630
  13.750   1.4524   0.04582   0.03915  -0.0868   0.0862   0.4655
  14.000   1.4470   0.04934   0.04273  -0.0865   0.0803   0.4683
  14.250   1.4394   0.05327   0.04673  -0.0865   0.0750   0.4713
  14.500   1.4327   0.05723   0.05077  -0.0866   0.0705   0.4743
  14.750   1.4272   0.06114   0.05476  -0.0869   0.0663   0.4776
  15.000   1.4174   0.06567   0.05933  -0.0874   0.0624   0.4805
  15.250   1.4133   0.06958   0.06331  -0.0879   0.0591   0.4836
  15.500   1.4087   0.07371   0.06753  -0.0887   0.0558   0.4871
  15.750   1.4006   0.07834   0.07222  -0.0896   0.0527   0.4903
  16.000   1.3984   0.08225   0.07622  -0.0904   0.0501   0.4943
  16.250   1.3964   0.08616   0.08019  -0.0913   0.0475   0.4985
  16.500   1.3914   0.09054   0.08461  -0.0924   0.0451   0.5021
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