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NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S804 Airfoil (s804-nr)
Reynolds number: 50,000
Max Cl/Cd: 22.22 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s804-nr-50000-n5.txt
Download as CSV file: xf-s804-nr-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S804 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2914   0.10307   0.09609  -0.0532   1.0000   0.0663
 -10.250  -0.3137   0.09540   0.08851  -0.0565   1.0000   0.0654
 -10.000  -0.3314   0.08931   0.08251  -0.0585   1.0000   0.0651
  -9.750  -0.3557   0.08319   0.07648  -0.0606   1.0000   0.0647
  -9.500  -0.3901   0.07731   0.07069  -0.0623   1.0000   0.0641
  -9.250  -0.4310   0.07301   0.06649  -0.0621   1.0000   0.0635
  -9.000  -0.4619   0.06644   0.05978  -0.0687   0.9864   0.0629
  -8.750  -0.4690   0.05902   0.05195  -0.0790   0.9619   0.0632
  -8.500  -0.4616   0.05347   0.04588  -0.0855   0.9424   0.0642
  -8.250  -0.4462   0.04911   0.04100  -0.0900   0.9250   0.0661
  -8.000  -0.4132   0.04673   0.03853  -0.0931   0.9128   0.0686
  -7.750  -0.3867   0.04385   0.03529  -0.0958   0.8981   0.0710
  -7.500  -0.3583   0.04100   0.03195  -0.0980   0.8837   0.0735
  -7.250  -0.3236   0.03933   0.03029  -0.0999   0.8708   0.0771
  -7.000  -0.2852   0.03722   0.02777  -0.1025   0.8597   0.0820
  -6.750  -0.2532   0.03586   0.02646  -0.1032   0.8451   0.0858
  -6.500  -0.2199   0.03447   0.02482  -0.1041   0.8312   0.0920
  -6.250  -0.1856   0.03323   0.02357  -0.1053   0.8184   0.0990
  -6.000  -0.1549   0.03207   0.02234  -0.1058   0.8041   0.1071
  -5.750  -0.1297   0.03107   0.02129  -0.1058   0.7883   0.1176
  -5.500  -0.1041   0.03000   0.02022  -0.1061   0.7736   0.1320
  -5.250  -0.0759   0.02879   0.01901  -0.1071   0.7605   0.1553
  -5.000  -0.0532   0.02764   0.01804  -0.1076   0.7457   0.1883
  -4.750  -0.0289   0.02648   0.01721  -0.1085   0.7320   0.2435
  -4.500  -0.0013   0.02592   0.01715  -0.1087   0.7204   0.3241
  -4.250   0.0213   0.02637   0.01779  -0.1071   0.7062   0.3887
  -4.000   0.0492   0.02689   0.01814  -0.1063   0.6944   0.4363
  -3.750   0.0768   0.02736   0.01837  -0.1057   0.6825   0.4721
  -3.500   0.1002   0.02799   0.01887  -0.1038   0.6710   0.4957
  -3.250   0.1257   0.02844   0.01914  -0.1022   0.6607   0.5173
  -3.000   0.1493   0.02880   0.01934  -0.1009   0.6499   0.5366
  -2.750   0.1747   0.02908   0.01943  -0.0997   0.6405   0.5538
  -2.500   0.1961   0.02942   0.01968  -0.0976   0.6309   0.5664
  -2.250   0.2216   0.02952   0.01960  -0.0969   0.6218   0.5814
  -2.000   0.2477   0.02963   0.01952  -0.0963   0.6138   0.5950
  -1.750   0.2691   0.02980   0.01962  -0.0949   0.6047   0.6053
  -1.500   0.2999   0.02973   0.01930  -0.0956   0.5977   0.6188
  -1.250   0.3194   0.02995   0.01949  -0.0938   0.5894   0.6265
  -1.000   0.3464   0.02997   0.01935  -0.0940   0.5817   0.6373
  -0.750   0.3744   0.02994   0.01914  -0.0937   0.5761   0.6454
  -0.500   0.3948   0.03019   0.01938  -0.0928   0.5681   0.6536
  -0.250   0.4227   0.03026   0.01931  -0.0934   0.5617   0.6624
   0.000   0.4497   0.03029   0.01920  -0.0930   0.5568   0.6692
   0.250   0.4733   0.03059   0.01945  -0.0931   0.5499   0.6771
   0.500   0.4981   0.03080   0.01960  -0.0930   0.5435   0.6841
   0.750   0.5253   0.03089   0.01957  -0.0929   0.5386   0.6906
   1.000   0.5541   0.03111   0.01967  -0.0936   0.5336   0.6983
   1.250   0.5739   0.03160   0.02021  -0.0930   0.5273   0.7045
   1.500   0.5981   0.03193   0.02050  -0.0927   0.5225   0.7113
   1.750   0.6292   0.03215   0.02059  -0.0938   0.5185   0.7190
   2.000   0.6551   0.03242   0.02080  -0.0936   0.5148   0.7253
   2.250   0.6702   0.03325   0.02174  -0.0925   0.5088   0.7325
   2.500   0.6946   0.03380   0.02228  -0.0928   0.5039   0.7406
   2.750   0.7189   0.03410   0.02255  -0.0923   0.5001   0.7474
   3.000   0.7498   0.03433   0.02268  -0.0930   0.4970   0.7559
   3.250   0.7631   0.03539   0.02386  -0.0918   0.4925   0.7637
   3.500   0.7748   0.03656   0.02515  -0.0905   0.4877   0.7725
   3.750   0.7940   0.03736   0.02599  -0.0900   0.4836   0.7816
   4.000   0.8179   0.03783   0.02645  -0.0897   0.4804   0.7913
   4.250   0.8462   0.03809   0.02668  -0.0898   0.4777   0.8017
   4.500   0.8480   0.03992   0.02867  -0.0878   0.4727   0.8131
   4.750   0.8412   0.04209   0.03105  -0.0849   0.4675   0.8245
   5.000   0.8487   0.04352   0.03257  -0.0833   0.4637   0.8380
   5.250   0.8665   0.04427   0.03337  -0.0824   0.4608   0.8540
   5.500   0.8929   0.04455   0.03366  -0.0822   0.4586   0.8742
   6.000   0.8064   0.05509   0.04471  -0.0757   0.4427   1.0000
   6.250   0.8396   0.05589   0.04546  -0.0775   0.4406   1.0000
   6.500   0.8767   0.05622   0.04572  -0.0790   0.4389   1.0000
   7.000   0.8161   0.07025   0.05992  -0.0816   0.4217   1.0000
   7.250   0.8484   0.07070   0.06031  -0.0822   0.4200   1.0000
   8.250   0.8197   0.08874   0.07849  -0.0863   0.3954   1.0000
   8.750   0.8419   0.09375   0.08352  -0.0874   0.3865   1.0000
   9.000   0.8688   0.09461   0.08438  -0.0875   0.3840   1.0000
   9.250   0.8448   0.10083   0.09068  -0.0891   0.3756   1.0000
   9.500   0.8559   0.10329   0.09318  -0.0896   0.3706   1.0000
   9.750   0.8788   0.10448   0.09438  -0.0896   0.3674   1.0000
  10.000   0.9067   0.10516   0.09506  -0.0895   0.3651   1.0000
  10.250   0.8766   0.11204   0.10206  -0.0916   0.3546   1.0000
  10.500   0.8968   0.11344   0.10349  -0.0916   0.3507   1.0000
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