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SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 50,000
Max Cl/Cd: 39.14 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7037-il-50000-n5.txt
Download as CSV file: xf-sd7037-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7037-092-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4012   0.08850   0.08174  -0.0383   1.0000   0.0519
  -7.750  -0.4024   0.08532   0.07865  -0.0382   1.0000   0.0515
  -7.500  -0.4034   0.08206   0.07547  -0.0385   1.0000   0.0511
  -7.250  -0.4050   0.07870   0.07218  -0.0391   1.0000   0.0505
  -7.000  -0.4069   0.07521   0.06874  -0.0399   1.0000   0.0498
  -6.750  -0.4087   0.07152   0.06508  -0.0408   1.0000   0.0490
  -6.500  -0.4097   0.06764   0.06119  -0.0417   1.0000   0.0482
  -6.250  -0.4090   0.06361   0.05711  -0.0428   1.0000   0.0473
  -6.000  -0.4061   0.05928   0.05267  -0.0439   1.0000   0.0463
  -5.750  -0.4002   0.05484   0.04801  -0.0452   1.0000   0.0454
  -5.500  -0.3908   0.05024   0.04310  -0.0464   1.0000   0.0445
  -5.250  -0.3776   0.04601   0.03847  -0.0474   1.0000   0.0439
  -5.000  -0.3612   0.04216   0.03415  -0.0479   1.0000   0.0437
  -4.750  -0.3424   0.03885   0.03037  -0.0482   1.0000   0.0437
  -4.500  -0.3219   0.03600   0.02707  -0.0481   1.0000   0.0441
  -4.250  -0.3006   0.03371   0.02440  -0.0479   1.0000   0.0455
  -4.000  -0.2783   0.03174   0.02201  -0.0476   1.0000   0.0482
  -3.750  -0.2547   0.02991   0.01970  -0.0471   1.0000   0.0508
  -3.500  -0.2313   0.02823   0.01768  -0.0464   1.0000   0.0530
  -3.250  -0.2088   0.02693   0.01627  -0.0457   1.0000   0.0557
  -3.000  -0.1861   0.02586   0.01503  -0.0449   1.0000   0.0600
  -2.750  -0.1510   0.02482   0.01385  -0.0465   0.9945   0.0706
  -2.500  -0.1130   0.02385   0.01269  -0.0485   0.9872   0.0909
  -2.250  -0.0748   0.02271   0.01184  -0.0511   0.9800   0.1498
  -2.000  -0.0360   0.02129   0.01129  -0.0541   0.9734   0.3095
  -1.750  -0.0073   0.02016   0.01126  -0.0543   0.9647   0.5574
  -1.500   0.0180   0.01945   0.01132  -0.0517   0.9562   0.8337
  -1.250   0.0702   0.01937   0.01086  -0.0564   0.9464   1.0000
  -1.000   0.1071   0.01957   0.01065  -0.0585   0.9349   1.0000
  -0.750   0.1448   0.01977   0.01051  -0.0607   0.9239   1.0000
  -0.500   0.1862   0.01995   0.01040  -0.0634   0.9141   1.0000
  -0.250   0.2216   0.02010   0.01031  -0.0651   0.9018   1.0000
   0.000   0.2564   0.02024   0.01025  -0.0665   0.8892   1.0000
   0.250   0.2917   0.02036   0.01021  -0.0679   0.8767   1.0000
   0.500   0.3264   0.02044   0.01014  -0.0690   0.8642   1.0000
   0.750   0.3610   0.02048   0.01007  -0.0701   0.8517   1.0000
   1.000   0.3956   0.02048   0.00997  -0.0710   0.8391   1.0000
   1.250   0.4286   0.02048   0.00989  -0.0715   0.8256   1.0000
   1.500   0.4596   0.02048   0.00984  -0.0717   0.8111   1.0000
   1.750   0.4904   0.02047   0.00979  -0.0717   0.7963   1.0000
   2.000   0.5210   0.02045   0.00973  -0.0717   0.7809   1.0000
   2.250   0.5495   0.02048   0.00973  -0.0713   0.7642   1.0000
   2.500   0.5782   0.02050   0.00976  -0.0709   0.7469   1.0000
   2.750   0.6071   0.02052   0.00976  -0.0705   0.7293   1.0000
   3.000   0.6362   0.02054   0.00977  -0.0701   0.7113   1.0000
   3.250   0.6656   0.02056   0.00976  -0.0696   0.6931   1.0000
   3.500   0.6925   0.02068   0.00990  -0.0689   0.6727   1.0000
   3.750   0.7192   0.02083   0.01004  -0.0681   0.6519   1.0000
   4.000   0.7470   0.02095   0.01012  -0.0674   0.6315   1.0000
   4.250   0.7716   0.02123   0.01045  -0.0665   0.6085   1.0000
   4.500   0.7980   0.02145   0.01064  -0.0656   0.5869   1.0000
   4.750   0.8218   0.02180   0.01101  -0.0646   0.5631   1.0000
   5.000   0.8467   0.02213   0.01131  -0.0636   0.5405   1.0000
   5.250   0.8700   0.02255   0.01179  -0.0626   0.5164   1.0000
   5.500   0.8934   0.02298   0.01221  -0.0616   0.4928   1.0000
   5.750   0.9164   0.02346   0.01270  -0.0605   0.4692   1.0000
   6.000   0.9386   0.02400   0.01330  -0.0594   0.4452   1.0000
   6.250   0.9610   0.02455   0.01384  -0.0583   0.4223   1.0000
   6.500   0.9821   0.02520   0.01454  -0.0572   0.3983   1.0000
   6.750   1.0034   0.02585   0.01520  -0.0561   0.3759   1.0000
   7.000   1.0236   0.02659   0.01603  -0.0549   0.3529   1.0000
   7.250   1.0437   0.02736   0.01680  -0.0537   0.3316   1.0000
   7.500   1.0629   0.02821   0.01774  -0.0525   0.3098   1.0000
   7.750   1.0817   0.02909   0.01863  -0.0512   0.2898   1.0000
   8.250   1.1170   0.03108   0.02083  -0.0485   0.2506   1.0000
   8.500   1.1336   0.03216   0.02196  -0.0471   0.2329   1.0000
   8.750   1.1491   0.03330   0.02313  -0.0457   0.2159   1.0000
   9.000   1.1636   0.03455   0.02453  -0.0442   0.1991   1.0000
   9.250   1.1765   0.03587   0.02600  -0.0425   0.1831   1.0000
   9.500   1.1886   0.03728   0.02752  -0.0409   0.1683   1.0000
   9.750   1.1986   0.03877   0.02913  -0.0390   0.1543   1.0000
  10.000   1.2076   0.04039   0.03086  -0.0372   0.1415   1.0000
  10.250   1.2134   0.04206   0.03260  -0.0350   0.1300   1.0000
  10.500   1.2178   0.04384   0.03442  -0.0329   0.1195   1.0000
  10.750   1.2191   0.04591   0.03670  -0.0308   0.1087   1.0000
  11.000   1.2185   0.04820   0.03916  -0.0289   0.0990   1.0000
  11.250   1.2150   0.05060   0.04166  -0.0273   0.0904   1.0000
  11.500   1.2101   0.05320   0.04434  -0.0261   0.0828   1.0000
  11.750   1.2045   0.05640   0.04776  -0.0254   0.0755   1.0000
  12.000   1.1984   0.05951   0.05085  -0.0250   0.0701   1.0000
  12.250   1.1920   0.06349   0.05514  -0.0250   0.0648   1.0000
  12.500   1.1858   0.06733   0.05909  -0.0254   0.0608   1.0000
  12.750   1.1797   0.07138   0.06320  -0.0261   0.0575   1.0000
  13.000   1.1698   0.07660   0.06877  -0.0274   0.0549   1.0000
  13.250   1.1592   0.08197   0.07438  -0.0291   0.0527   1.0000
  13.500   1.1491   0.08742   0.07999  -0.0312   0.0510   1.0000
  13.750   1.1427   0.09214   0.08475  -0.0331   0.0491   1.0000
  14.000   1.1327   0.09795   0.09068  -0.0355   0.0480   1.0000
  14.250   1.1143   0.10597   0.09897  -0.0398   0.0477   1.0000
  14.500   1.0938   0.11497   0.10820  -0.0450   0.0476   1.0000
  14.750   1.0730   0.12468   0.11808  -0.0506   0.0479   1.0000
  15.000   1.0516   0.13532   0.12883  -0.0568   0.0483   1.0000
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