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NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S811 Airfoil (s811-nr)
Reynolds number: 200,000
Max Cl/Cd: 52.28 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s811-nr-200000-n5.txt
Download as CSV file: xf-s811-nr-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3818   0.10944   0.10350  -0.0229   1.0000   0.2665
 -11.000  -0.3645   0.10880   0.10289  -0.0225   1.0000   0.2670
 -10.750  -0.3478   0.10811   0.10222  -0.0220   1.0000   0.2675
 -10.500  -0.3308   0.10749   0.10163  -0.0216   1.0000   0.2682
 -10.250  -0.3151   0.10675   0.10092  -0.0211   1.0000   0.2689
 -10.000  -0.2830   0.10462   0.09878  -0.0249   0.9934   0.2699
  -9.000  -0.1128   0.08748   0.08046  -0.0632   0.7175   0.2806
  -8.750  -0.0950   0.08690   0.07958  -0.0629   0.6630   0.2811
  -8.500  -0.0783   0.08624   0.07873  -0.0624   0.6287   0.2817
  -8.250  -0.0623   0.08539   0.07774  -0.0622   0.6036   0.2824
  -8.000  -0.0462   0.08452   0.07676  -0.0620   0.5843   0.2832
  -7.750  -0.0316   0.08346   0.07560  -0.0619   0.5691   0.2842
  -7.500  -0.0181   0.08227   0.07432  -0.0619   0.5561   0.2855
  -7.000  -0.0391   0.07532   0.06722  -0.0629   0.5422   0.2936
  -6.750  -0.0202   0.07466   0.06649  -0.0627   0.5324   0.2941
  -6.500  -0.0016   0.07388   0.06568  -0.0626   0.5236   0.2945
  -6.250   0.0165   0.07315   0.06490  -0.0624   0.5155   0.2951
  -6.000   0.0346   0.07240   0.06411  -0.0623   0.5087   0.2957
  -5.750   0.0511   0.07145   0.06314  -0.0622   0.5025   0.2964
  -4.750   0.0478   0.06157   0.05309  -0.0625   0.4866   0.3072
  -4.500   0.0665   0.06091   0.05242  -0.0623   0.4816   0.3076
  -4.250   0.0849   0.06030   0.05179  -0.0620   0.4770   0.3081
  -4.000   0.1028   0.05966   0.05112  -0.0616   0.4731   0.3086
  -3.750   0.1218   0.05907   0.05053  -0.0613   0.4696   0.3092
  -3.500   0.1407   0.05850   0.04998  -0.0611   0.4661   0.3099
  -2.500  -0.0544   0.03455   0.02589  -0.0570   0.4629   0.3361
  -2.250  -0.0358   0.03412   0.02548  -0.0566   0.4598   0.3367
  -2.000  -0.0171   0.03368   0.02503  -0.0563   0.4569   0.3372
  -1.750   0.0006   0.03310   0.02443  -0.0562   0.4543   0.3379
  -1.500   0.0168   0.03219   0.02349  -0.0566   0.4519   0.3390
  -1.250   0.0117   0.02765   0.01876  -0.0613   0.4502   0.3440
  -1.000   0.0234   0.02432   0.01508  -0.0655   0.4480   0.3492
  -0.750   0.0480   0.02308   0.01363  -0.0673   0.4455   0.3511
  -0.500   0.0752   0.02278   0.01333  -0.0678   0.4429   0.3519
  -0.250   0.1028   0.02266   0.01324  -0.0679   0.4405   0.3526
   0.000   0.1304   0.02257   0.01317  -0.0681   0.4381   0.3532
   0.250   0.1582   0.02252   0.01312  -0.0683   0.4358   0.3539
   0.500   0.1863   0.02249   0.01307  -0.0686   0.4335   0.3546
   0.750   0.2145   0.02243   0.01303  -0.0689   0.4315   0.3554
   1.000   0.2427   0.02234   0.01299  -0.0692   0.4296   0.3563
   1.250   0.2710   0.02223   0.01292  -0.0696   0.4277   0.3572
   1.500   0.2995   0.02212   0.01283  -0.0701   0.4257   0.3583
   1.750   0.3282   0.02200   0.01272  -0.0706   0.4238   0.3594
   2.000   0.3570   0.02188   0.01260  -0.0711   0.4220   0.3608
   2.250   0.3861   0.02175   0.01247  -0.0717   0.4203   0.3623
   2.500   0.4155   0.02162   0.01231  -0.0724   0.4186   0.3639
   2.750   0.4452   0.02149   0.01212  -0.0731   0.4171   0.3655
   3.000   0.4753   0.02139   0.01195  -0.0739   0.4155   0.3668
   3.250   0.5050   0.02137   0.01189  -0.0745   0.4137   0.3678
   3.500   0.5333   0.02138   0.01199  -0.0747   0.4120   0.3687
   3.750   0.5614   0.02142   0.01214  -0.0748   0.4105   0.3695
   4.000   0.5896   0.02150   0.01232  -0.0749   0.4089   0.3705
   4.250   0.6178   0.02159   0.01250  -0.0751   0.4073   0.3714
   4.500   0.6461   0.02168   0.01268  -0.0752   0.4057   0.3724
   4.750   0.6744   0.02177   0.01285  -0.0754   0.4039   0.3736
   5.000   0.7028   0.02185   0.01298  -0.0755   0.4019   0.3748
   5.250   0.7314   0.02193   0.01311  -0.0758   0.4002   0.3760
   5.500   0.7602   0.02203   0.01324  -0.0760   0.3987   0.3774
   5.750   0.7892   0.02213   0.01336  -0.0763   0.3970   0.3791
   6.000   0.8188   0.02226   0.01348  -0.0767   0.3952   0.3808
   6.250   0.8476   0.02243   0.01367  -0.0770   0.3934   0.3824
   6.500   0.8740   0.02254   0.01387  -0.0769   0.3911   0.3838
   6.750   0.9000   0.02262   0.01408  -0.0767   0.3883   0.3850
   7.000   0.9260   0.02270   0.01429  -0.0764   0.3853   0.3861
   7.250   0.9526   0.02277   0.01446  -0.0762   0.3823   0.3873
   7.500   0.9797   0.02282   0.01456  -0.0760   0.3793   0.3885
   7.750   1.0082   0.02287   0.01460  -0.0760   0.3759   0.3898
   8.000   1.0301   0.02295   0.01486  -0.0750   0.3714   0.3911
   8.250   1.0530   0.02296   0.01499  -0.0741   0.3661   0.3925
   8.500   1.0775   0.02289   0.01496  -0.0735   0.3611   0.3940
   8.750   1.1031   0.02287   0.01493  -0.0730   0.3565   0.3957
   9.000   1.1228   0.02297   0.01521  -0.0717   0.3504   0.3974
   9.250   1.1441   0.02295   0.01525  -0.0706   0.3439   0.3992
   9.500   1.1649   0.02296   0.01527  -0.0694   0.3370   0.4008
   9.750   1.1826   0.02301   0.01545  -0.0678   0.3272   0.4023
  10.000   1.1986   0.02306   0.01560  -0.0659   0.3165   0.4037
  10.250   1.2102   0.02315   0.01575  -0.0633   0.3042   0.4050
  10.500   1.2207   0.02340   0.01605  -0.0607   0.2892   0.4062
  10.750   1.2295   0.02385   0.01650  -0.0581   0.2703   0.4075
  11.000   1.2314   0.02464   0.01720  -0.0548   0.2486   0.4088
  11.250   1.2271   0.02586   0.01831  -0.0513   0.2281   0.4099
  11.500   1.2189   0.02748   0.01987  -0.0480   0.2097   0.4109
  11.750   1.2099   0.02942   0.02178  -0.0453   0.1944   0.4120
  12.000   1.1994   0.03177   0.02414  -0.0433   0.1804   0.4131
  12.250   1.1873   0.03463   0.02701  -0.0420   0.1679   0.4141
  12.500   1.1744   0.03796   0.03036  -0.0414   0.1571   0.4150
  12.750   1.1600   0.04179   0.03423  -0.0414   0.1478   0.4159
  13.000   1.1465   0.04580   0.03828  -0.0418   0.1385   0.4168
  13.250   1.1332   0.04996   0.04247  -0.0424   0.1303   0.4178
  13.500   1.1194   0.05429   0.04682  -0.0432   0.1228   0.4186
  13.750   1.1097   0.05829   0.05084  -0.0440   0.1150   0.4196
  14.000   1.0993   0.06244   0.05502  -0.0450   0.1081   0.4206
  14.250   1.0918   0.06639   0.05902  -0.0460   0.1010   0.4217
  14.500   1.0862   0.07024   0.06291  -0.0471   0.0946   0.4228
  14.750   1.0803   0.07423   0.06692  -0.0483   0.0884   0.4240
  15.000   1.0783   0.07781   0.07055  -0.0494   0.0821   0.4253
  15.250   1.0753   0.08162   0.07438  -0.0506   0.0767   0.4266
  15.500   1.0740   0.08526   0.07805  -0.0519   0.0712   0.4280
  15.750   1.0734   0.08888   0.08170  -0.0531   0.0663   0.4294
  16.250   1.0736   0.09606   0.08894  -0.0558   0.0575   0.4324
  16.500   1.0731   0.09984   0.09275  -0.0573   0.0541   0.4338
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