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NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S811 Airfoil (s811-nr)
Reynolds number: 500,000
Max Cl/Cd: 75.97 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s811-nr-500000-n5.txt
Download as CSV file: xf-s811-nr-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.9216   0.02770   0.02288  -0.0499   0.9537   0.3071
 -10.000  -0.8979   0.02660   0.02177  -0.0517   0.9354   0.3080
  -9.750  -0.7515   0.02693   0.02154  -0.0717   0.7888   0.3081
  -9.500  -0.7521   0.02599   0.02033  -0.0696   0.7224   0.3091
  -9.250  -0.7562   0.02453   0.01868  -0.0681   0.6824   0.3101
  -9.000  -0.7648   0.02270   0.01671  -0.0666   0.6536   0.3112
  -8.750  -0.7803   0.02077   0.01464  -0.0645   0.6309   0.3123
  -8.500  -0.7788   0.01933   0.01305  -0.0644   0.6087   0.3134
  -8.250  -0.7641   0.01855   0.01212  -0.0648   0.5875   0.3143
  -8.000  -0.7450   0.01807   0.01151  -0.0649   0.5687   0.3151
  -7.750  -0.7241   0.01766   0.01099  -0.0649   0.5521   0.3158
  -7.500  -0.7014   0.01730   0.01052  -0.0651   0.5382   0.3165
  -7.250  -0.6777   0.01697   0.01009  -0.0654   0.5262   0.3172
  -7.000  -0.6533   0.01667   0.00969  -0.0656   0.5148   0.3178
  -6.750  -0.6280   0.01639   0.00932  -0.0660   0.5053   0.3185
  -6.500  -0.6022   0.01613   0.00898  -0.0663   0.4959   0.3191
  -6.250  -0.5759   0.01590   0.00866  -0.0667   0.4881   0.3196
  -6.000  -0.5490   0.01567   0.00835  -0.0671   0.4804   0.3202
  -5.750  -0.5221   0.01548   0.00807  -0.0675   0.4733   0.3207
  -5.500  -0.4944   0.01529   0.00781  -0.0679   0.4676   0.3211
  -5.250  -0.4668   0.01509   0.00757  -0.0683   0.4618   0.3217
  -5.000  -0.4391   0.01492   0.00736  -0.0686   0.4560   0.3225
  -4.750  -0.4112   0.01478   0.00719  -0.0690   0.4509   0.3232
  -4.500  -0.3827   0.01464   0.00704  -0.0694   0.4464   0.3239
  -4.250  -0.3541   0.01453   0.00691  -0.0698   0.4418   0.3245
  -4.000  -0.3256   0.01443   0.00678  -0.0702   0.4376   0.3252
  -3.750  -0.2970   0.01435   0.00666  -0.0706   0.4338   0.3258
  -3.500  -0.2680   0.01426   0.00655  -0.0710   0.4308   0.3265
  -3.250  -0.2388   0.01416   0.00644  -0.0715   0.4280   0.3272
  -3.000  -0.2096   0.01408   0.00634  -0.0719   0.4250   0.3280
  -2.750  -0.1803   0.01401   0.00625  -0.0724   0.4221   0.3288
  -2.500  -0.1511   0.01395   0.00617  -0.0728   0.4193   0.3296
  -2.250  -0.1220   0.01390   0.00608  -0.0732   0.4167   0.3305
  -2.000  -0.0928   0.01386   0.00600  -0.0736   0.4141   0.3314
  -1.750  -0.0633   0.01379   0.00592  -0.0740   0.4122   0.3322
  -1.500  -0.0336   0.01372   0.00583  -0.0745   0.4104   0.3329
  -1.250  -0.0040   0.01365   0.00575  -0.0749   0.4085   0.3336
  -1.000   0.0257   0.01359   0.00568  -0.0754   0.4064   0.3343
  -0.750   0.0553   0.01355   0.00562  -0.0758   0.4043   0.3350
  -0.500   0.0849   0.01351   0.00556  -0.0762   0.4020   0.3355
  -0.250   0.1145   0.01349   0.00550  -0.0765   0.4000   0.3360
   0.000   0.1438   0.01343   0.00545  -0.0769   0.3982   0.3370
   0.250   0.1731   0.01340   0.00543  -0.0772   0.3964   0.3379
   0.500   0.2024   0.01341   0.00544  -0.0776   0.3946   0.3387
   0.750   0.2322   0.01340   0.00545  -0.0779   0.3933   0.3396
   1.000   0.2620   0.01338   0.00547  -0.0783   0.3922   0.3404
   1.250   0.2918   0.01338   0.00550  -0.0786   0.3909   0.3413
   1.500   0.3216   0.01338   0.00553  -0.0790   0.3896   0.3421
   1.750   0.3514   0.01339   0.00556  -0.0793   0.3882   0.3430
   2.000   0.3811   0.01341   0.00560  -0.0796   0.3869   0.3440
   2.250   0.4108   0.01343   0.00565  -0.0799   0.3855   0.3450
   2.500   0.4404   0.01347   0.00569  -0.0802   0.3842   0.3461
   2.750   0.4699   0.01351   0.00575  -0.0805   0.3827   0.3472
   3.000   0.4993   0.01355   0.00579  -0.0807   0.3812   0.3481
   3.250   0.5287   0.01360   0.00584  -0.0810   0.3796   0.3491
   3.500   0.5580   0.01366   0.00591  -0.0812   0.3782   0.3498
   3.750   0.5873   0.01375   0.00599  -0.0814   0.3768   0.3505
   4.000   0.6167   0.01386   0.00610  -0.0816   0.3754   0.3512
   4.250   0.6463   0.01388   0.00617  -0.0819   0.3746   0.3522
   4.500   0.6758   0.01390   0.00626  -0.0821   0.3737   0.3533
   4.750   0.7051   0.01394   0.00637  -0.0823   0.3725   0.3544
   5.000   0.7344   0.01399   0.00648  -0.0825   0.3711   0.3554
   5.250   0.7636   0.01405   0.00661  -0.0826   0.3697   0.3564
   5.500   0.7926   0.01412   0.00673  -0.0827   0.3682   0.3575
   5.750   0.8214   0.01418   0.00684  -0.0828   0.3662   0.3586
   6.000   0.8498   0.01424   0.00694  -0.0828   0.3637   0.3597
   6.250   0.8779   0.01432   0.00703  -0.0827   0.3610   0.3609
   6.500   0.9057   0.01445   0.00716  -0.0826   0.3581   0.3621
   6.750   0.9337   0.01450   0.00728  -0.0825   0.3552   0.3634
   7.000   0.9615   0.01450   0.00735  -0.0823   0.3507   0.3646
   7.250   0.9884   0.01452   0.00738  -0.0820   0.3449   0.3657
   7.500   1.0142   0.01461   0.00745  -0.0816   0.3389   0.3665
   7.750   1.0419   0.01463   0.00755  -0.0814   0.3328   0.3673
   8.000   1.0681   0.01468   0.00763  -0.0810   0.3259   0.3686
   8.250   1.0942   0.01477   0.00777  -0.0806   0.3193   0.3699
   8.500   1.1195   0.01487   0.00790  -0.0801   0.3086   0.3712
   8.750   1.1433   0.01505   0.00807  -0.0793   0.2940   0.3724
   9.000   1.1622   0.01541   0.00834  -0.0778   0.2692   0.3736
   9.250   1.1747   0.01608   0.00885  -0.0755   0.2388   0.3747
   9.500   1.1818   0.01685   0.00948  -0.0723   0.2120   0.3757
   9.750   1.1885   0.01765   0.01018  -0.0692   0.1895   0.3768
  10.000   1.1948   0.01855   0.01100  -0.0662   0.1684   0.3779
  10.250   1.2003   0.01951   0.01188  -0.0632   0.1503   0.3790
  10.500   1.2059   0.02048   0.01279  -0.0604   0.1355   0.3801
  10.750   1.2105   0.02151   0.01378  -0.0577   0.1223   0.3812
  11.000   1.2145   0.02261   0.01486  -0.0551   0.1111   0.3822
  11.250   1.2173   0.02385   0.01609  -0.0527   0.1015   0.3830
  11.500   1.2186   0.02527   0.01752  -0.0505   0.0935   0.3837
  11.750   1.2180   0.02697   0.01923  -0.0486   0.0865   0.3845
  12.000   1.2166   0.02895   0.02125  -0.0472   0.0801   0.3857
  12.250   1.2142   0.03126   0.02362  -0.0463   0.0744   0.3867
  12.500   1.2090   0.03408   0.02649  -0.0458   0.0695   0.3877
  12.750   1.2054   0.03701   0.02949  -0.0457   0.0648   0.3886
  13.000   1.1989   0.04039   0.03293  -0.0458   0.0608   0.3895
  13.250   1.1925   0.04389   0.03649  -0.0462   0.0569   0.3904
  13.500   1.1858   0.04747   0.04014  -0.0466   0.0538   0.3913
  13.750   1.1790   0.05112   0.04385  -0.0471   0.0505   0.3922
  14.000   1.1711   0.05495   0.04773  -0.0478   0.0473   0.3930
  14.250   1.1658   0.05854   0.05138  -0.0484   0.0445   0.3940
  14.500   1.1608   0.06219   0.05507  -0.0492   0.0418   0.3949
  14.750   1.1572   0.06579   0.05872  -0.0501   0.0391   0.3959
  15.000   1.1539   0.06943   0.06240  -0.0510   0.0367   0.3969
  15.250   1.1532   0.07283   0.06585  -0.0519   0.0343   0.3979
  15.500   1.1515   0.07645   0.06950  -0.0530   0.0324   0.3989
  15.750   1.1526   0.07973   0.07283  -0.0539   0.0306   0.3999
  16.000   1.1530   0.08318   0.07631  -0.0550   0.0291   0.4009
  16.250   1.1540   0.08660   0.07978  -0.0561   0.0277   0.4018
  16.500   1.1570   0.08979   0.08303  -0.0572   0.0266   0.4034
  16.750   1.1581   0.09331   0.08661  -0.0585   0.0256   0.4050
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