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NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S801 Airfoil (s801-nr)
Reynolds number: 50,000
Max Cl/Cd: 31.68 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s801-nr-50000.txt
Download as CSV file: xf-s801-nr-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3725   0.11527   0.11005  -0.0125   1.0000   0.2949
  -7.500  -0.3596   0.11184   0.10663  -0.0108   1.0000   0.3027
  -7.250  -0.3918   0.11103   0.10594  -0.0092   1.0000   0.3122
  -7.000  -0.3731   0.10766   0.10255  -0.0074   1.0000   0.3237
  -6.750  -0.3753   0.10516   0.10009  -0.0056   1.0000   0.3343
  -6.500  -0.3928   0.10329   0.09829  -0.0036   1.0000   0.3459
  -6.250  -0.4116   0.10195   0.09703  -0.0010   1.0000   0.3594
  -6.000  -0.4124   0.09953   0.09464   0.0013   1.0000   0.3752
  -5.750  -0.4161   0.09722   0.09238   0.0038   1.0000   0.3913
  -5.500  -0.4235   0.09507   0.09029   0.0065   1.0000   0.4076
  -5.000  -0.5441   0.06258   0.05568  -0.0440   1.0000   0.1537
  -4.750  -0.5194   0.05649   0.04907  -0.0469   1.0000   0.1375
  -4.500  -0.4985   0.05270   0.04510  -0.0479   1.0000   0.1337
  -4.250  -0.4722   0.04899   0.04087  -0.0500   1.0000   0.1316
  -4.000  -0.4445   0.04590   0.03724  -0.0517   1.0000   0.1310
  -3.750  -0.4164   0.04324   0.03403  -0.0529   1.0000   0.1302
  -3.500  -0.3891   0.04110   0.03142  -0.0535   1.0000   0.1308
  -3.250  -0.3627   0.03944   0.02936  -0.0538   1.0000   0.1337
  -3.000  -0.3373   0.03813   0.02769  -0.0538   1.0000   0.1401
  -2.750  -0.3146   0.03708   0.02659  -0.0532   1.0000   0.1489
  -2.500  -0.2921   0.03609   0.02551  -0.0522   1.0000   0.1583
  -2.250  -0.2713   0.03533   0.02481  -0.0509   1.0000   0.1761
  -2.000  -0.2489   0.03447   0.02411  -0.0498   1.0000   0.2148
  -1.750  -0.2281   0.03162   0.02445  -0.0471   1.0000   0.5734
  -1.500  -0.2477   0.03267   0.02574  -0.0337   1.0000   0.7943
  -1.250  -0.2641   0.03266   0.02570  -0.0224   1.0000   0.8655
  -1.000  -0.2666   0.03202   0.02497  -0.0139   1.0000   0.9503
  -0.750  -0.2211   0.03198   0.02447  -0.0187   1.0000   1.0000
  -0.500  -0.2058   0.03199   0.02418  -0.0185   1.0000   1.0000
  -0.250  -0.1871   0.03221   0.02410  -0.0189   1.0000   1.0000
   0.000  -0.1661   0.03257   0.02418  -0.0196   1.0000   1.0000
   0.250  -0.1438   0.03307   0.02442  -0.0206   1.0000   1.0000
   0.500  -0.1207   0.03365   0.02477  -0.0217   1.0000   1.0000
   0.750  -0.0973   0.03432   0.02521  -0.0229   1.0000   1.0000
   1.000  -0.0736   0.03505   0.02575  -0.0241   1.0000   1.0000
   1.250  -0.0500   0.03585   0.02638  -0.0254   1.0000   1.0000
   1.500  -0.0265   0.03671   0.02708  -0.0266   1.0000   1.0000
   1.750  -0.0032   0.03762   0.02785  -0.0278   1.0000   1.0000
   2.000   0.0198   0.03859   0.02869  -0.0291   1.0000   1.0000
   2.250   0.0426   0.03961   0.02960  -0.0303   1.0000   1.0000
   2.500   0.0649   0.04069   0.03058  -0.0314   1.0000   1.0000
   2.750   0.0869   0.04182   0.03162  -0.0326   1.0000   1.0000
   3.000   0.1085   0.04300   0.03274  -0.0338   1.0000   1.0000
   3.250   0.1296   0.04424   0.03392  -0.0349   1.0000   1.0000
   3.500   0.1502   0.04554   0.03517  -0.0360   1.0000   1.0000
   3.750   0.1704   0.04689   0.03649  -0.0371   1.0000   1.0000
   4.000   0.1902   0.04831   0.03788  -0.0382   1.0000   1.0000
   4.250   0.2094   0.04979   0.03935  -0.0392   1.0000   1.0000
   4.500   0.2301   0.05145   0.04101  -0.0407   0.9987   1.0000
   4.750   0.2661   0.05421   0.04378  -0.0451   0.9883   1.0000
   5.000   0.3012   0.05696   0.04655  -0.0494   0.9756   1.0000
   5.250   0.3386   0.05993   0.04955  -0.0539   0.9612   1.0000
   5.500   0.3658   0.06207   0.05174  -0.0567   0.9447   1.0000
   5.750   0.3969   0.06432   0.05408  -0.0599   0.9234   1.0000
   6.000   0.4369   0.06752   0.05734  -0.0644   0.9032   1.0000
   6.250   0.4655   0.06928   0.05919  -0.0667   0.8759   1.0000
   6.500   0.5817   0.06798   0.05801  -0.0730   0.7564   1.0000
   6.750   0.6268   0.06880   0.05897  -0.0750   0.7302   1.0000
   7.000   0.6570   0.06961   0.05991  -0.0757   0.7064   1.0000
   7.250   0.6969   0.07011   0.06054  -0.0768   0.6836   1.0000
   7.500   0.7249   0.07069   0.06130  -0.0768   0.6606   1.0000
   7.750   0.7824   0.06981   0.06063  -0.0784   0.6400   1.0000
   8.000   0.7945   0.07068   0.06163  -0.0770   0.6154   1.0000
   8.250   0.8547   0.06835   0.05959  -0.0775   0.5948   1.0000
   8.500   0.8742   0.06836   0.05977  -0.0760   0.5696   1.0000
   8.750   0.9494   0.06289   0.05470  -0.0753   0.5497   1.0000
   9.000   0.9831   0.06043   0.05250  -0.0730   0.5233   1.0000
   9.250   1.0591   0.05193   0.04442  -0.0698   0.4988   1.0000
   9.500   1.1793   0.03867   0.03123  -0.0669   0.4346   1.0000
   9.750   1.2100   0.03819   0.03001  -0.0643   0.3617   1.0000
  10.000   1.2287   0.03979   0.03108  -0.0624   0.3105   1.0000
  10.250   1.2515   0.04174   0.03266  -0.0615   0.2708   1.0000
  10.500   1.2795   0.04383   0.03457  -0.0614   0.2395   1.0000
  10.750   1.3190   0.04624   0.03678  -0.0628   0.2131   1.0000
  11.000   1.3430   0.04878   0.03942  -0.0627   0.1957   1.0000
  11.250   1.3717   0.05172   0.04247  -0.0632   0.1817   1.0000
  11.500   1.3988   0.05476   0.04560  -0.0637   0.1696   1.0000
  11.750   1.4021   0.05768   0.04890  -0.0613   0.1630   1.0000
  12.000   1.4258   0.06141   0.05275  -0.0616   0.1554   1.0000
  12.250   1.4114   0.06454   0.05633  -0.0575   0.1526   1.0000
  12.500   1.4011   0.06786   0.05997  -0.0544   0.1492   1.0000
  12.750   1.4313   0.07207   0.06416  -0.0555   0.1424   1.0000
  13.000   1.4073   0.07582   0.06829  -0.0517   0.1419   1.0000
  13.250   1.3809   0.08005   0.07287  -0.0486   0.1416   1.0000
  13.500   1.3528   0.08487   0.07799  -0.0464   0.1416   1.0000
  13.750   1.3231   0.09034   0.08372  -0.0451   0.1418   1.0000
  14.000   1.2927   0.09651   0.09012  -0.0449   0.1422   1.0000
  14.250   1.2631   0.10340   0.09720  -0.0456   0.1428   1.0000
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