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NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S811 Airfoil (s811-nr)
Reynolds number: 500,000
Max Cl/Cd: 79.07 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s811-nr-500000.txt
Download as CSV file: xf-s811-nr-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0240   0.09571   0.09114  -0.0600   0.6931   0.2725
  -9.500  -0.0201   0.09399   0.08919  -0.0598   0.6500   0.2765
  -9.250  -0.0204   0.09148   0.08654  -0.0600   0.6228   0.2817
  -9.000  -0.0443   0.09043   0.08548  -0.0677   0.6983   0.2829
  -8.750  -0.0257   0.09062   0.08537  -0.0664   0.6381   0.2841
  -8.500  -0.0054   0.09059   0.08517  -0.0658   0.6016   0.2863
  -8.250  -0.0855   0.08047   0.07502  -0.0682   0.6120   0.2937
  -8.000  -0.0619   0.08021   0.07462  -0.0677   0.5831   0.2941
  -7.750  -0.0322   0.08057   0.07487  -0.0672   0.5593   0.2945
  -7.500  -0.0031   0.08073   0.07493  -0.0668   0.5411   0.2950
  -7.250   0.0299   0.08136   0.07549  -0.0664   0.5260   0.2958
  -7.000   0.0662   0.08250   0.07655  -0.0659   0.5119   0.2975
  -6.750   0.0826   0.08140   0.07543  -0.0660   0.5044   0.2984
  -6.500   0.1011   0.08073   0.07471  -0.0659   0.4968   0.3004
  -6.250   0.0951   0.07837   0.07230  -0.0662   0.4920   0.3048
  -6.000  -0.4857   0.02313   0.01688  -0.0678   0.5474   0.3346
  -5.750  -0.4742   0.02197   0.01553  -0.0681   0.5354   0.3356
  -5.500  -0.4586   0.02065   0.01406  -0.0684   0.5253   0.3370
  -5.250  -0.4352   0.02015   0.01349  -0.0684   0.5151   0.3379
  -5.000  -0.4095   0.01986   0.01317  -0.0686   0.5066   0.3385
  -4.750  -0.3835   0.01964   0.01290  -0.0687   0.4984   0.3391
  -4.500  -0.3573   0.01949   0.01268  -0.0689   0.4913   0.3397
  -4.250  -0.3302   0.01926   0.01245  -0.0692   0.4857   0.3403
  -4.000  -0.3033   0.01909   0.01224  -0.0694   0.4802   0.3409
  -3.750  -0.2765   0.01893   0.01202  -0.0697   0.4749   0.3416
  -3.500  -0.2493   0.01875   0.01179  -0.0700   0.4705   0.3423
  -3.250  -0.2217   0.01850   0.01153  -0.0704   0.4667   0.3431
  -3.000  -0.1940   0.01828   0.01127  -0.0708   0.4628   0.3439
  -2.750  -0.1663   0.01807   0.01100  -0.0713   0.4591   0.3447
  -2.500  -0.1386   0.01787   0.01074  -0.0717   0.4555   0.3456
  -2.250  -0.1106   0.01771   0.01050  -0.0722   0.4519   0.3465
  -2.000  -0.0820   0.01747   0.01025  -0.0727   0.4497   0.3474
  -1.750  -0.0532   0.01726   0.01001  -0.0732   0.4471   0.3483
  -1.500  -0.0243   0.01708   0.00979  -0.0737   0.4444   0.3492
  -1.250   0.0047   0.01692   0.00958  -0.0742   0.4416   0.3499
  -1.000   0.0338   0.01682   0.00943  -0.0747   0.4389   0.3506
  -0.750   0.0631   0.01680   0.00935  -0.0751   0.4364   0.3511
  -0.500   0.0917   0.01638   0.00887  -0.0758   0.4337   0.3527
  -0.250   0.1208   0.01623   0.00873  -0.0763   0.4318   0.3538
   0.000   0.1501   0.01613   0.00868  -0.0766   0.4303   0.3546
   0.250   0.1796   0.01608   0.00866  -0.0770   0.4286   0.3554
   0.500   0.2090   0.01605   0.00866  -0.0773   0.4268   0.3562
   0.750   0.2386   0.01602   0.00866  -0.0777   0.4250   0.3570
   1.000   0.2682   0.01601   0.00866  -0.0780   0.4232   0.3579
   1.250   0.2978   0.01600   0.00866  -0.0784   0.4215   0.3588
   1.500   0.3275   0.01599   0.00865  -0.0788   0.4199   0.3598
   1.750   0.3573   0.01600   0.00864  -0.0792   0.4183   0.3608
   2.000   0.3872   0.01603   0.00866  -0.0797   0.4164   0.3618
   2.250   0.4176   0.01615   0.00874  -0.0802   0.4140   0.3629
   2.500   0.4477   0.01620   0.00880  -0.0807   0.4126   0.3639
   2.750   0.4775   0.01618   0.00881  -0.0811   0.4116   0.3649
   3.000   0.5073   0.01619   0.00884  -0.0815   0.4104   0.3658
   3.250   0.5371   0.01622   0.00889  -0.0818   0.4092   0.3666
   3.500   0.5670   0.01629   0.00898  -0.0822   0.4078   0.3672
   3.750   0.5968   0.01606   0.00877  -0.0827   0.4064   0.3690
   4.000   0.6263   0.01602   0.00878  -0.0830   0.4048   0.3704
   4.250   0.6556   0.01606   0.00887  -0.0832   0.4031   0.3715
   4.500   0.6852   0.01614   0.00899  -0.0835   0.4017   0.3726
   4.750   0.7147   0.01622   0.00911  -0.0837   0.4002   0.3737
   5.000   0.7443   0.01631   0.00923  -0.0840   0.3986   0.3748
   5.250   0.7741   0.01647   0.00939  -0.0843   0.3967   0.3759
   5.500   0.8045   0.01684   0.00977  -0.0848   0.3941   0.3772
   5.750   0.8328   0.01680   0.00981  -0.0848   0.3927   0.3784
   6.000   0.8609   0.01678   0.00985  -0.0847   0.3908   0.3797
   6.250   0.8892   0.01679   0.00991  -0.0847   0.3885   0.3809
   6.500   0.9175   0.01678   0.00994  -0.0847   0.3858   0.3820
   6.750   0.9457   0.01673   0.00990  -0.0846   0.3825   0.3830
   7.000   0.9737   0.01671   0.00985  -0.0844   0.3785   0.3838
   7.250   1.0014   0.01670   0.00984  -0.0844   0.3740   0.3852
   7.500   1.0269   0.01641   0.00966  -0.0839   0.3698   0.3871
   7.750   1.0530   0.01629   0.00960  -0.0834   0.3654   0.3887
   8.000   1.0793   0.01624   0.00958  -0.0829   0.3613   0.3901
   8.250   1.1062   0.01638   0.00972  -0.0827   0.3567   0.3915
   8.500   1.1308   0.01627   0.00974  -0.0819   0.3525   0.3929
   8.750   1.1558   0.01620   0.00974  -0.0812   0.3472   0.3943
   9.000   1.1804   0.01620   0.00975  -0.0805   0.3420   0.3958
   9.250   1.2053   0.01626   0.00986  -0.0798   0.3370   0.3973
   9.500   1.2302   0.01625   0.00993  -0.0792   0.3304   0.3987
   9.750   1.2525   0.01633   0.00999  -0.0781   0.3231   0.3999
  10.000   1.2767   0.01639   0.01014  -0.0773   0.3141   0.4010
  10.250   1.2971   0.01654   0.01027  -0.0759   0.3027   0.4019
  10.500   1.3141   0.01662   0.01035  -0.0741   0.2857   0.4042
  10.750   1.3219   0.01708   0.01071  -0.0710   0.2598   0.4058
  11.000   1.3241   0.01799   0.01148  -0.0673   0.2318   0.4071
  11.250   1.3239   0.01913   0.01250  -0.0635   0.2075   0.4083
  11.500   1.3235   0.02032   0.01361  -0.0600   0.1859   0.4096
  11.750   1.3212   0.02165   0.01487  -0.0565   0.1674   0.4109
  12.000   1.3173   0.02315   0.01631  -0.0533   0.1515   0.4121
  12.250   1.3121   0.02486   0.01799  -0.0505   0.1377   0.4132
  12.500   1.3054   0.02688   0.02000  -0.0481   0.1258   0.4143
  12.750   1.2976   0.02927   0.02240  -0.0463   0.1157   0.4154
  13.000   1.2878   0.03218   0.02533  -0.0452   0.1071   0.4163
  13.250   1.2757   0.03568   0.02885  -0.0448   0.0994   0.4171
  13.500   1.2662   0.03924   0.03246  -0.0448   0.0925   0.4180
  13.750   1.2523   0.04342   0.03668  -0.0451   0.0866   0.4187
  14.000   1.2391   0.04766   0.04096  -0.0456   0.0805   0.4192
  14.250   1.2263   0.05194   0.04529  -0.0463   0.0754   0.4198
  14.500   1.2127   0.05638   0.04975  -0.0471   0.0704   0.4205
  14.750   1.2026   0.06053   0.05395  -0.0480   0.0652   0.4219
  15.000   1.1916   0.06492   0.05838  -0.0490   0.0602   0.4232
  15.250   1.1815   0.06933   0.06282  -0.0502   0.0552   0.4243
  15.500   1.1756   0.07336   0.06688  -0.0513   0.0504   0.4255
  15.750   1.1689   0.07760   0.07116  -0.0526   0.0466   0.4266
  16.000   1.1645   0.08159   0.07517  -0.0539   0.0434   0.4279
  16.250   1.1612   0.08558   0.07920  -0.0552   0.0406   0.4291
  16.500   1.1593   0.08939   0.08304  -0.0565   0.0384   0.4306
  16.750   1.1566   0.09341   0.08710  -0.0579   0.0367   0.4320
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