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NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S801 Airfoil (s801-nr)
Reynolds number: 50,000
Max Cl/Cd: 27.14 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s801-nr-50000-n5.txt
Download as CSV file: xf-s801-nr-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S801 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2702   0.13463   0.12833  -0.0418   1.0000   0.1162
 -11.250  -0.2778   0.13300   0.12679  -0.0404   1.0000   0.1157
 -11.000  -0.3591   0.12418   0.11713  -0.0549   1.0000   0.0671
 -10.750  -0.3445   0.12147   0.11438  -0.0521   1.0000   0.0645
 -10.500  -0.3460   0.11851   0.11150  -0.0514   1.0000   0.0626
 -10.250  -0.3521   0.11551   0.10861  -0.0509   1.0000   0.0611
  -9.750  -0.3978   0.10706   0.10046  -0.0526   1.0000   0.0551
  -9.500  -0.4081   0.10499   0.09849  -0.0506   1.0000   0.0549
  -9.250  -0.4225   0.10275   0.09637  -0.0488   1.0000   0.0547
  -9.000  -0.4215   0.09812   0.09177  -0.0523   0.9954   0.0545
  -8.750  -0.4172   0.09228   0.08592  -0.0581   0.9880   0.0544
  -8.500  -0.4193   0.08587   0.07949  -0.0647   0.9791   0.0542
  -8.250  -0.4249   0.08070   0.07428  -0.0695   0.9691   0.0538
  -8.000  -0.4299   0.07508   0.06855  -0.0750   0.9589   0.0535
  -7.750  -0.4328   0.06992   0.06320  -0.0789   0.9489   0.0533
  -7.500  -0.4359   0.06515   0.05817  -0.0814   0.9392   0.0532
  -7.250  -0.4290   0.06015   0.05278  -0.0846   0.9324   0.0532
  -7.000  -0.4235   0.05621   0.04847  -0.0855   0.9242   0.0531
  -6.750  -0.4052   0.05190   0.04365  -0.0882   0.9194   0.0533
  -6.500  -0.3942   0.04882   0.04011  -0.0881   0.9125   0.0536
  -6.250  -0.3723   0.04556   0.03623  -0.0894   0.9077   0.0545
  -6.000  -0.3446   0.04299   0.03335  -0.0913   0.9044   0.0569
  -5.750  -0.3275   0.04149   0.03165  -0.0906   0.8983   0.0592
  -5.500  -0.3021   0.03961   0.02942  -0.0911   0.8939   0.0613
  -5.250  -0.2721   0.03774   0.02716  -0.0920   0.8908   0.0634
  -5.000  -0.2417   0.03621   0.02522  -0.0925   0.8881   0.0660
  -4.750  -0.2261   0.03537   0.02434  -0.0908   0.8824   0.0694
  -4.500  -0.2010   0.03453   0.02340  -0.0906   0.8785   0.0751
  -4.250  -0.1720   0.03359   0.02227  -0.0905   0.8755   0.0811
  -4.000  -0.1445   0.03277   0.02139  -0.0907   0.8725   0.0897
  -3.750  -0.1304   0.03233   0.02097  -0.0889   0.8670   0.1008
  -3.500  -0.1065   0.03158   0.02026  -0.0888   0.8633   0.1244
  -3.250  -0.0789   0.03047   0.01955  -0.0898   0.8603   0.1834
  -3.000  -0.0486   0.02877   0.01900  -0.0921   0.8581   0.3644
  -2.750  -0.0480   0.02866   0.01991  -0.0864   0.8523   0.5298
  -2.500  -0.0431   0.02944   0.02096  -0.0800   0.8477   0.6582
  -2.250  -0.0231   0.03015   0.02142  -0.0776   0.8443   0.7343
  -2.000  -0.0124   0.03073   0.02185  -0.0733   0.8401   0.7737
  -1.750  -0.0082   0.03121   0.02221  -0.0683   0.8347   0.8039
  -1.500   0.0030   0.03145   0.02231  -0.0643   0.8308   0.8336
  -1.250   0.0187   0.03152   0.02222  -0.0611   0.8277   0.8624
  -1.000   0.0247   0.03168   0.02228  -0.0570   0.8227   0.8871
  -0.750   0.0386   0.03174   0.02221  -0.0542   0.8181   0.9121
  -0.500   0.0711   0.03181   0.02210  -0.0550   0.8151   0.9380
  -0.250   0.1222   0.03201   0.02208  -0.0596   0.8130   0.9597
   0.000   0.1789   0.03225   0.02209  -0.0657   0.8112   0.9738
   0.250   0.2089   0.03277   0.02250  -0.0679   0.8057   0.9876
   0.500   0.2365   0.03310   0.02271  -0.0693   0.8011   1.0000
   0.750   0.2563   0.03328   0.02277  -0.0687   0.7972   1.0000
   1.000   0.2600   0.03372   0.02315  -0.0659   0.7908   1.0000
   1.250   0.2760   0.03413   0.02348  -0.0651   0.7852   1.0000
   1.500   0.3052   0.03445   0.02370  -0.0662   0.7816   1.0000
   1.750   0.3216   0.03504   0.02423  -0.0656   0.7756   1.0000
   2.000   0.3432   0.03558   0.02472  -0.0657   0.7698   1.0000
   2.250   0.3759   0.03596   0.02504  -0.0673   0.7660   1.0000
   2.500   0.3944   0.03667   0.02572  -0.0671   0.7594   1.0000
   2.750   0.4198   0.03725   0.02627  -0.0677   0.7534   1.0000
   3.000   0.4554   0.03761   0.02661  -0.0695   0.7496   1.0000
   3.500   0.5018   0.03894   0.02795  -0.0702   0.7359   1.0000
   4.000   0.5514   0.04022   0.02930  -0.0712   0.7217   1.0000
   4.250   0.5907   0.04039   0.02950  -0.0731   0.7177   1.0000
   4.500   0.6033   0.04140   0.03057  -0.0722   0.7067   1.0000
   4.750   0.6432   0.04144   0.03069  -0.0740   0.7022   1.0000
   5.000   0.6569   0.04243   0.03175  -0.0731   0.6907   1.0000
   5.500   0.7127   0.04320   0.03271  -0.0739   0.6738   1.0000
   5.750   0.7327   0.04387   0.03349  -0.0735   0.6627   1.0000
   6.000   0.7727   0.04348   0.03322  -0.0747   0.6564   1.0000
   6.250   0.7902   0.04412   0.03398  -0.0739   0.6433   1.0000
   6.500   0.8112   0.04453   0.03453  -0.0733   0.6306   1.0000
   7.000   0.8766   0.04353   0.03385  -0.0732   0.6100   1.0000
   7.250   0.8978   0.04354   0.03404  -0.0722   0.5952   1.0000
   7.500   0.9203   0.04335   0.03401  -0.0711   0.5801   1.0000
   7.750   0.9440   0.04290   0.03373  -0.0699   0.5644   1.0000
   8.000   0.9510   0.04386   0.03484  -0.0680   0.5421   1.0000
   8.250   0.9736   0.04338   0.03455  -0.0667   0.5235   1.0000
   8.500   0.9970   0.04281   0.03415  -0.0653   0.5027   1.0000
   8.750   1.0197   0.04235   0.03383  -0.0639   0.4776   1.0000
   9.000   1.0484   0.04133   0.03289  -0.0625   0.4471   1.0000
   9.250   1.0766   0.04046   0.03195  -0.0609   0.4084   1.0000
   9.500   1.0977   0.04044   0.03168  -0.0592   0.3645   1.0000
   9.750   1.1086   0.04155   0.03253  -0.0574   0.3241   1.0000
  10.000   1.1146   0.04325   0.03402  -0.0556   0.2890   1.0000
  10.250   1.1194   0.04518   0.03577  -0.0541   0.2594   1.0000
  10.500   1.1240   0.04726   0.03771  -0.0527   0.2336   1.0000
  10.750   1.1296   0.04934   0.03969  -0.0515   0.2117   1.0000
  11.000   1.1365   0.05141   0.04170  -0.0505   0.1928   1.0000
  11.250   1.1440   0.05347   0.04371  -0.0496   0.1763   1.0000
  11.500   1.1535   0.05545   0.04570  -0.0488   0.1623   1.0000
  11.750   1.1639   0.05740   0.04766  -0.0480   0.1498   1.0000
  12.000   1.1756   0.05929   0.04955  -0.0473   0.1391   1.0000
  12.250   1.1891   0.06106   0.05133  -0.0466   0.1296   1.0000
  12.500   1.2030   0.06296   0.05342  -0.0461   0.1205   1.0000
  12.750   1.2190   0.06466   0.05513  -0.0455   0.1130   1.0000
  13.000   1.2337   0.06667   0.05740  -0.0450   0.1061   1.0000
  13.250   1.2498   0.06849   0.05922  -0.0445   0.1002   1.0000
  13.500   1.2586   0.07117   0.06225  -0.0441   0.0949   1.0000
  13.750   1.2718   0.07337   0.06455  -0.0437   0.0905   1.0000
  14.000   1.2824   0.07604   0.06738  -0.0434   0.0866   1.0000
  14.250   1.2805   0.07982   0.07155  -0.0432   0.0833   1.0000
  14.500   1.2803   0.08338   0.07535  -0.0432   0.0803   1.0000
  14.750   1.2853   0.08645   0.07857  -0.0432   0.0777   1.0000
  15.000   1.2893   0.08984   0.08208  -0.0433   0.0754   1.0000
  15.250   1.2713   0.09565   0.08829  -0.0444   0.0743   1.0000
  15.500   1.2507   0.10210   0.09510  -0.0463   0.0733   1.0000
  15.750   1.2269   0.10944   0.10276  -0.0491   0.0727   1.0000
  16.000   1.1982   0.11821   0.11180  -0.0533   0.0725   1.0000
  16.250   1.1621   0.12944   0.12324  -0.0598   0.0729   1.0000
  16.500   1.1177   0.14445   0.13841  -0.0694   0.0738   1.0000
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