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NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S811 Airfoil (s811-nr)
Reynolds number: 200,000
Max Cl/Cd: 48.78 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s811-nr-200000.txt
Download as CSV file: xf-s811-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S811 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1690   0.11945   0.11412  -0.0152   1.0000   0.3243
  -9.000  -0.1542   0.11813   0.11286  -0.0146   1.0000   0.3255
  -8.750  -0.1414   0.11686   0.11163  -0.0141   1.0000   0.3270
  -8.500  -0.1139   0.11430   0.10910  -0.0177   0.9963   0.3294
  -7.750   0.0690   0.09777   0.09127  -0.0621   0.7105   0.3378
  -7.500   0.0872   0.09658   0.08971  -0.0613   0.6594   0.3385
  -7.250   0.1050   0.09540   0.08832  -0.0609   0.6313   0.3393
  -7.000   0.1228   0.09425   0.08701  -0.0607   0.6113   0.3406
  -6.750   0.1392   0.09311   0.08575  -0.0606   0.5964   0.3420
  -6.500   0.0662   0.09606   0.08868  -0.0596   0.5969   0.3515
  -6.250   0.0956   0.09319   0.08573  -0.0599   0.5834   0.3517
  -6.000   0.1238   0.09075   0.08316  -0.0603   0.5724   0.3521
  -5.750   0.1500   0.08864   0.08103  -0.0606   0.5627   0.3525
  -5.500   0.1743   0.08688   0.07917  -0.0608   0.5546   0.3529
  -5.250   0.1977   0.08531   0.07759  -0.0609   0.5475   0.3536
  -5.000   0.2194   0.08393   0.07619  -0.0610   0.5413   0.3544
  -4.750   0.2399   0.08273   0.07493  -0.0611   0.5359   0.3554
  -4.500   0.2590   0.08163   0.07378  -0.0611   0.5312   0.3567
  -4.250   0.2765   0.08053   0.07270  -0.0612   0.5267   0.3584
  -4.000   0.2044   0.08252   0.07469  -0.0594   0.5271   0.3676
  -3.750   0.2337   0.08012   0.07229  -0.0598   0.5222   0.3680
  -3.500   0.2617   0.07812   0.07027  -0.0601   0.5181   0.3683
  -3.250   0.2891   0.07641   0.06851  -0.0605   0.5142   0.3688
  -3.000   0.3150   0.07493   0.06702  -0.0607   0.5109   0.3693
  -2.750   0.3388   0.07359   0.06574  -0.0608   0.5076   0.3700
  -2.500   0.3611   0.07242   0.06460  -0.0608   0.5043   0.3709
  -2.250   0.3820   0.07137   0.06356  -0.0607   0.5010   0.3720
  -2.000   0.4013   0.07040   0.06260  -0.0606   0.4981   0.3734
  -1.750   0.3163   0.07300   0.06523  -0.0575   0.4983   0.3842
  -1.500   0.3480   0.07046   0.06266  -0.0579   0.4953   0.3846
  -1.250   0.3778   0.06867   0.06084  -0.0583   0.4928   0.3850
  -1.000   0.4052   0.06717   0.05940  -0.0585   0.4905   0.3854
  -0.750   0.4320   0.06581   0.05811  -0.0585   0.4881   0.3860
  -0.500   0.4572   0.06465   0.05702  -0.0584   0.4857   0.3866
  -0.250   0.4809   0.06363   0.05605  -0.0583   0.4834   0.3874
   0.000   0.5031   0.06273   0.05520  -0.0581   0.4813   0.3884
   0.250   0.5236   0.06192   0.05442  -0.0578   0.4793   0.3897
   0.500   0.5424   0.06117   0.05370  -0.0575   0.4774   0.3914
   0.750   0.5587   0.06050   0.05304  -0.0571   0.4755   0.3939
   1.000   0.4950   0.05999   0.05257  -0.0537   0.4752   0.4027
   1.250   0.5249   0.05885   0.05142  -0.0540   0.4729   0.4032
   1.500   0.5519   0.05792   0.05056  -0.0539   0.4711   0.4038
   1.750   0.5758   0.05706   0.04981  -0.0535   0.4694   0.4045
   2.000   0.5980   0.05633   0.04918  -0.0530   0.4677   0.4053
   2.250   0.6195   0.05570   0.04865  -0.0524   0.4659   0.4064
   2.500   0.6384   0.05512   0.04817  -0.0517   0.4642   0.4079
   2.750   0.6549   0.05458   0.04771  -0.0509   0.4622   0.4098
   3.000   0.6665   0.05407   0.04726  -0.0497   0.4603   0.4131
   3.250   0.6010   0.05334   0.04658  -0.0449   0.4598   0.4215
   3.500   0.6263   0.05264   0.04594  -0.0440   0.4578   0.4222
   3.750   0.6508   0.05208   0.04544  -0.0432   0.4562   0.4231
   4.000   0.6728   0.05159   0.04500  -0.0425   0.4547   0.4240
   4.250   0.6940   0.05129   0.04472  -0.0418   0.4529   0.4253
   4.500   0.7081   0.05104   0.04459  -0.0404   0.4510   0.4271
   4.750   0.7174   0.05078   0.04449  -0.0386   0.4493   0.4295
   5.000   0.6871   0.04626   0.03991  -0.0437   0.4482   0.4169
   5.250   0.6998   0.04539   0.03917  -0.0424   0.4459   0.4133
   5.500   0.7160   0.04543   0.03932  -0.0419   0.4435   0.4242
   5.750   0.7347   0.04531   0.03928  -0.0406   0.4411   0.4257
   6.000   0.7549   0.04531   0.03935  -0.0393   0.4386   0.4284
   6.250   0.7801   0.04699   0.04114  -0.0350   0.4361   0.4455
   6.500   0.8019   0.04664   0.04079  -0.0350   0.4339   0.4482
   6.750   0.8165   0.04618   0.04041  -0.0355   0.4314   0.4504
   7.000   0.8968   0.03308   0.02630  -0.0709   0.4273   0.4198
   7.250   0.9211   0.03280   0.02612  -0.0710   0.4236   0.4213
   7.500   0.9489   0.03256   0.02594  -0.0710   0.4199   0.4226
   7.750   0.9812   0.03218   0.02556  -0.0715   0.4163   0.4241
   8.000   1.0116   0.03219   0.02555  -0.0718   0.4124   0.4257
   8.250   1.0264   0.03230   0.02589  -0.0700   0.4069   0.4272
   8.500   1.0537   0.03192   0.02556  -0.0698   0.4016   0.4293
   8.750   1.0897   0.03119   0.02472  -0.0708   0.3970   0.4320
   9.000   1.1203   0.03086   0.02435  -0.0714   0.3921   0.4345
   9.250   1.1398   0.03058   0.02416  -0.0704   0.3855   0.4365
   9.500   1.1739   0.02964   0.02308  -0.0711   0.3792   0.4385
   9.750   1.2015   0.02887   0.02230  -0.0709   0.3726   0.4403
  10.000   1.2173   0.02842   0.02201  -0.0689   0.3649   0.4419
  10.250   1.2471   0.02765   0.02117  -0.0687   0.3585   0.4438
  10.500   1.2597   0.02764   0.02136  -0.0663   0.3519   0.4454
  10.750   1.2763   0.02736   0.02117  -0.0644   0.3447   0.4474
  11.000   1.2955   0.02703   0.02085  -0.0629   0.3378   0.4499
  11.250   1.2999   0.02707   0.02107  -0.0594   0.3293   0.4519
  11.500   1.3108   0.02687   0.02085  -0.0567   0.3210   0.4542
  11.750   1.3166   0.02717   0.02126  -0.0538   0.3096   0.4561
  12.000   1.3232   0.02759   0.02171  -0.0512   0.2961   0.4576
  12.250   1.3262   0.02809   0.02222  -0.0486   0.2786   0.4592
  12.500   1.3213   0.02913   0.02320  -0.0455   0.2589   0.4606
  12.750   1.3085   0.03098   0.02497  -0.0424   0.2393   0.4617
  13.000   1.2906   0.03365   0.02759  -0.0401   0.2219   0.4626
  13.250   1.2694   0.03714   0.03105  -0.0387   0.2063   0.4635
  13.500   1.2466   0.04135   0.03524  -0.0383   0.1927   0.4642
  13.750   1.2233   0.04606   0.03995  -0.0386   0.1799   0.4650
  14.000   1.2019   0.05091   0.04480  -0.0393   0.1675   0.4658
  14.250   1.1815   0.05584   0.04973  -0.0402   0.1560   0.4667
  14.500   1.1626   0.06078   0.05464  -0.0413   0.1454   0.4676
  14.750   1.1447   0.06579   0.05960  -0.0427   0.1353   0.4685
  15.000   1.1313   0.07050   0.06429  -0.0440   0.1246   0.4697
  15.250   1.1208   0.07501   0.06877  -0.0455   0.1146   0.4711
  15.500   1.1110   0.07955   0.07327  -0.0470   0.1054   0.4726
  15.750   1.1020   0.08410   0.07773  -0.0486   0.0970   0.4740
  16.000   1.0956   0.08841   0.08198  -0.0501   0.0891   0.4756
  16.250   1.0915   0.09251   0.08605  -0.0516   0.0814   0.4770
  16.500   1.0893   0.09635   0.08986  -0.0531   0.0751   0.4788
  16.750   1.0881   0.09997   0.09342  -0.0545   0.0699   0.4806
  17.000   1.0904   0.10328   0.09680  -0.0557   0.0652   0.4826
  17.250   1.0938   0.10623   0.09964  -0.0567   0.0616   0.4847
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