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NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S818 Airfoil (s818-nr)
Reynolds number: 200,000
Max Cl/Cd: 57.7 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s818-nr-200000.txt
Download as CSV file: xf-s818-nr-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3338   0.11505   0.11023  -0.0240   1.0000   0.3571
 -10.500  -0.3215   0.11402   0.10919  -0.0230   1.0000   0.3599
 -10.250  -0.3702   0.11393   0.10910  -0.0216   1.0000   0.3688
 -10.000  -0.3504   0.11181   0.10697  -0.0209   1.0000   0.3693
  -9.750  -0.3333   0.11014   0.10528  -0.0199   1.0000   0.3700
  -9.500  -0.3186   0.10883   0.10396  -0.0188   1.0000   0.3708
  -9.250  -0.3060   0.10782   0.10295  -0.0174   1.0000   0.3720
  -9.000  -0.2769   0.10590   0.10099  -0.0202   0.9975   0.3735
  -8.750  -0.3193   0.10704   0.10205  -0.0260   0.9904   0.3843
  -8.500  -0.2788   0.10361   0.09857  -0.0296   0.9866   0.3845
  -8.250  -0.2367   0.10041   0.09531  -0.0335   0.9835   0.3849
  -8.000  -0.1966   0.09759   0.09244  -0.0376   0.9812   0.3853
  -7.750  -0.1639   0.09509   0.08990  -0.0403   0.9757   0.3857
  -7.500  -0.1279   0.09267   0.08745  -0.0438   0.9717   0.3862
  -7.250  -0.0894   0.09035   0.08508  -0.0480   0.9689   0.3870
  -7.000  -0.0589   0.08827   0.08299  -0.0505   0.9627   0.3879
  -6.750  -0.0255   0.08612   0.08081  -0.0540   0.9575   0.3889
  -6.500   0.0102   0.08393   0.07859  -0.0583   0.9543   0.3901
  -6.250   0.0323   0.08213   0.07679  -0.0594   0.9439   0.3915
  -6.000   0.0636   0.08006   0.07470  -0.0631   0.9391   0.3934
  -5.750   0.0085   0.08044   0.07505  -0.0619   0.9143   0.4008
  -5.500   0.0359   0.07808   0.07269  -0.0627   0.9009   0.4010
  -5.250   0.0660   0.07573   0.07033  -0.0638   0.8870   0.4014
  -5.000   0.1024   0.07326   0.06783  -0.0665   0.8741   0.4017
  -4.750   0.1492   0.07050   0.06501  -0.0716   0.8610   0.4022
  -4.500   0.2125   0.06735   0.06174  -0.0807   0.8442   0.4027
  -4.250   0.3084   0.06346   0.05762  -0.0976   0.8185   0.4035
  -4.000   0.3799   0.06084   0.05464  -0.1092   0.7746   0.4044
  -3.750   0.4097   0.05980   0.05330  -0.1113   0.7349   0.4055
  -3.500   0.4279   0.05913   0.05241  -0.1109   0.7057   0.4067
  -3.250   0.3535   0.06152   0.05471  -0.1053   0.6897   0.4169
  -3.000   0.3779   0.06000   0.05305  -0.1050   0.6695   0.4172
  -2.750   0.4017   0.05867   0.05161  -0.1047   0.6520   0.4175
  -2.500   0.4251   0.05749   0.05032  -0.1043   0.6369   0.4178
  -2.250   0.4476   0.05644   0.04917  -0.1039   0.6239   0.4182
  -2.000   0.4689   0.05550   0.04817  -0.1034   0.6116   0.4187
  -1.750   0.4900   0.05463   0.04725  -0.1029   0.6007   0.4193
  -1.500   0.5113   0.05387   0.04639  -0.1026   0.5915   0.4200
  -1.250   0.5296   0.05314   0.04568  -0.1017   0.5820   0.4209
  -1.000   0.5490   0.05249   0.04494  -0.1014   0.5745   0.4220
  -0.750   0.5648   0.05188   0.04435  -0.1004   0.5667   0.4234
  -0.500   0.5798   0.05129   0.04374  -0.0996   0.5603   0.4253
  -0.250   0.5912   0.05081   0.04321  -0.0987   0.5550   0.4283
   0.000   0.5350   0.05031   0.04280  -0.0920   0.5519   0.4345
   0.250   0.5604   0.04938   0.04187  -0.0920   0.5460   0.4349
   0.500   0.5876   0.04855   0.04098  -0.0924   0.5411   0.4355
   0.750   0.6106   0.04785   0.04030  -0.0922   0.5365   0.4363
   1.000   0.6314   0.04723   0.03974  -0.0915   0.5318   0.4372
   1.250   0.6523   0.04668   0.03920  -0.0909   0.5275   0.4386
   1.500   0.6719   0.04617   0.03867  -0.0905   0.5240   0.4405
   1.750   0.6836   0.04577   0.03828  -0.0891   0.5206   0.4433
   2.000   0.6354   0.04478   0.03737  -0.0852   0.5186   0.4514
   2.250   0.6543   0.04413   0.03678  -0.0838   0.5147   0.4519
   2.500   0.6752   0.04354   0.03623  -0.0829   0.5112   0.4526
   2.750   0.6974   0.04298   0.03567  -0.0824   0.5083   0.4534
   3.000   0.7218   0.04249   0.03516  -0.0827   0.5056   0.4544
   3.250   0.7374   0.04203   0.03479  -0.0816   0.5030   0.4557
   3.500   0.7504   0.04151   0.03437  -0.0804   0.5003   0.4571
   3.750   0.7643   0.04093   0.03386  -0.0798   0.4976   0.4590
   4.000   0.7792   0.04010   0.03307  -0.0803   0.4951   0.4604
   4.250   0.8836   0.02393   0.01568  -0.1280   0.4920   0.4213
   4.500   0.9153   0.02407   0.01582  -0.1291   0.4895   0.4228
   4.750   0.9463   0.02427   0.01604  -0.1302   0.4871   0.4246
   5.000   0.9724   0.02438   0.01627  -0.1303   0.4847   0.4266
   5.250   1.0007   0.02449   0.01646  -0.1310   0.4822   0.4291
   5.500   1.0313   0.02461   0.01659  -0.1322   0.4798   0.4318
   5.750   1.0619   0.02470   0.01671  -0.1333   0.4773   0.4340
   6.000   1.0907   0.02483   0.01692  -0.1337   0.4749   0.4357
   6.250   1.1210   0.02510   0.01725  -0.1345   0.4728   0.4375
   6.500   1.1532   0.02552   0.01771  -0.1356   0.4706   0.4396
   6.750   1.1739   0.02577   0.01815  -0.1347   0.4677   0.4417
   7.000   1.1975   0.02603   0.01854  -0.1343   0.4644   0.4440
   7.250   1.2244   0.02625   0.01883  -0.1345   0.4612   0.4467
   7.500   1.2550   0.02640   0.01898  -0.1354   0.4579   0.4495
   7.750   1.2878   0.02637   0.01891  -0.1364   0.4526   0.4520
   8.000   1.3010   0.02624   0.01898  -0.1338   0.4451   0.4539
   8.250   1.3322   0.02593   0.01861  -0.1342   0.4382   0.4567
   8.500   1.3519   0.02615   0.01896  -0.1330   0.4332   0.4596
   8.750   1.3707   0.02625   0.01920  -0.1316   0.4279   0.4629
   9.000   1.4007   0.02615   0.01901  -0.1320   0.4223   0.4667
   9.250   1.4219   0.02621   0.01920  -0.1310   0.4169   0.4694
   9.500   1.4347   0.02627   0.01946  -0.1284   0.4108   0.4719
   9.750   1.4610   0.02612   0.01930  -0.1281   0.4048   0.4753
  10.000   1.4744   0.02628   0.01960  -0.1257   0.3989   0.4785
  10.250   1.4864   0.02629   0.01971  -0.1231   0.3923   0.4819
  10.500   1.5088   0.02615   0.01951  -0.1221   0.3855   0.4854
  10.750   1.5054   0.02637   0.02000  -0.1170   0.3790   0.4876
  11.000   1.5164   0.02641   0.02010  -0.1142   0.3715   0.4907
  11.250   1.5195   0.02678   0.02064  -0.1104   0.3637   0.4941
  11.500   1.5259   0.02705   0.02095  -0.1072   0.3547   0.4982
  11.750   1.5271   0.02765   0.02171  -0.1036   0.3446   0.5017
  12.000   1.5290   0.02823   0.02243  -0.1002   0.3331   0.5048
  12.250   1.5278   0.02911   0.02344  -0.0967   0.3185   0.5080
  12.500   1.5240   0.03034   0.02476  -0.0933   0.2975   0.5115
  12.750   1.5125   0.03223   0.02656  -0.0896   0.2690   0.5147
  13.000   1.4909   0.03522   0.02936  -0.0859   0.2411   0.5171
  13.250   1.4664   0.03902   0.03306  -0.0830   0.2171   0.5190
  13.500   1.4410   0.04345   0.03744  -0.0809   0.1973   0.5206
  13.750   1.4175   0.04826   0.04223  -0.0798   0.1792   0.5223
  14.000   1.3945   0.05345   0.04740  -0.0793   0.1637   0.5241
  14.250   1.3727   0.05886   0.05280  -0.0793   0.1506   0.5261
  14.500   1.3534   0.06425   0.05818  -0.0798   0.1390   0.5284
  14.750   1.3389   0.06931   0.06325  -0.0805   0.1282   0.5313
  15.000   1.3259   0.07433   0.06825  -0.0813   0.1191   0.5345
  15.250   1.3138   0.07931   0.07321  -0.0823   0.1110   0.5371
  15.500   1.3082   0.08356   0.07753  -0.0831   0.1031   0.5405
  15.750   1.2996   0.08816   0.08208  -0.0841   0.0966   0.5442
  16.000   1.2996   0.09186   0.08586  -0.0851   0.0901   0.5495
  16.250   1.2960   0.09592   0.08987  -0.0862   0.0846   0.5540
  16.500   1.2979   0.09932   0.09339  -0.0871   0.0794   0.5589
  16.750   1.2985   0.10295   0.09704  -0.0882   0.0749   0.5649
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