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SG6040 (sg6040-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SG6040 (sg6040-il)
Reynolds number: 50,000
Max Cl/Cd: 26.06 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6040-il-50000.txt
Download as CSV file: xf-sg6040-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6040                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4932   0.08981   0.08306  -0.0591   1.0000   0.1396
  -9.750  -0.4557   0.09033   0.08359  -0.0536   1.0000   0.1442
  -9.500  -0.5100   0.08199   0.07539  -0.0568   1.0000   0.1352
  -9.250  -0.6489   0.07664   0.07001  -0.0535   1.0000   0.1245
  -9.000  -0.6626   0.07339   0.06676  -0.0509   1.0000   0.1238
  -8.750  -0.6794   0.07018   0.06351  -0.0483   1.0000   0.1230
  -8.500  -0.6962   0.06685   0.06007  -0.0458   1.0000   0.1222
  -8.250  -0.7119   0.06336   0.05640  -0.0433   1.0000   0.1216
  -8.000  -0.7230   0.05979   0.05257  -0.0412   1.0000   0.1211
  -7.750  -0.7296   0.05619   0.04863  -0.0393   1.0000   0.1209
  -7.500  -0.7304   0.05270   0.04475  -0.0376   1.0000   0.1213
  -7.250  -0.7268   0.04937   0.04093  -0.0361   1.0000   0.1226
  -7.000  -0.7193   0.04631   0.03735  -0.0348   1.0000   0.1255
  -6.750  -0.7047   0.04439   0.03555  -0.0336   1.0000   0.1319
  -6.500  -0.6915   0.04194   0.03253  -0.0324   1.0000   0.1388
  -6.250  -0.6757   0.04000   0.03065  -0.0313   1.0000   0.1487
  -6.000  -0.6595   0.03805   0.02853  -0.0302   1.0000   0.1617
  -5.750  -0.6431   0.03642   0.02686  -0.0290   1.0000   0.1805
  -5.500  -0.6262   0.03487   0.02516  -0.0280   1.0000   0.2049
  -5.250  -0.6097   0.03355   0.02408  -0.0267   1.0000   0.2317
  -5.000  -0.5926   0.03235   0.02302  -0.0255   1.0000   0.2603
  -4.750  -0.5756   0.03129   0.02212  -0.0243   1.0000   0.2922
  -4.500  -0.5587   0.03031   0.02139  -0.0229   1.0000   0.3283
  -4.250  -0.5422   0.02936   0.02086  -0.0214   1.0000   0.3757
  -4.000  -0.5287   0.02886   0.02112  -0.0187   1.0000   0.4478
  -3.750  -0.5208   0.02981   0.02268  -0.0132   1.0000   0.5417
  -3.500  -0.5154   0.03130   0.02428  -0.0069   1.0000   0.6109
  -3.250  -0.5103   0.03252   0.02544  -0.0009   1.0000   0.6595
  -3.000  -0.5061   0.03347   0.02635   0.0052   1.0000   0.6951
  -2.750  -0.5021   0.03418   0.02699   0.0110   1.0000   0.7260
  -2.500  -0.4983   0.03467   0.02741   0.0167   1.0000   0.7539
  -2.250  -0.4933   0.03494   0.02756   0.0216   1.0000   0.7825
  -2.000  -0.4884   0.03514   0.02768   0.0266   1.0000   0.8088
  -1.750  -0.4819   0.03524   0.02768   0.0310   1.0000   0.8354
  -1.500  -0.4467   0.03648   0.02873   0.0307   0.9883   0.8680
  -1.250  -0.3829   0.03837   0.03034   0.0257   0.9748   0.9045
  -1.000  -0.2055   0.04221   0.03360  -0.0004   0.9567   0.9440
  -0.750  -0.1075   0.04322   0.03431  -0.0152   0.9445   0.9614
  -0.500  -0.0417   0.04371   0.03461  -0.0246   0.9334   0.9748
  -0.250   0.0227   0.04421   0.03496  -0.0339   0.9227   0.9861
   0.000   0.0910   0.04476   0.03536  -0.0438   0.9125   0.9965
   0.250   0.1090   0.04499   0.03553  -0.0449   0.9020   1.0000
   0.500   0.1268   0.04533   0.03580  -0.0455   0.8923   1.0000
   0.750   0.1352   0.04560   0.03603  -0.0446   0.8825   1.0000
   1.000   0.1407   0.04593   0.03632  -0.0433   0.8731   1.0000
   1.250   0.1565   0.04632   0.03667  -0.0434   0.8638   1.0000
   1.500   0.1499   0.04657   0.03691  -0.0401   0.8547   1.0000
   1.750   0.1699   0.04705   0.03733  -0.0408   0.8458   1.0000
   2.000   0.1512   0.04717   0.03745  -0.0357   0.8377   1.0000
   2.250   0.1651   0.04759   0.03783  -0.0354   0.8291   1.0000
   2.500   0.1462   0.04764   0.03786  -0.0305   0.8218   1.0000
   2.750   0.1556   0.04812   0.03830  -0.0297   0.8138   1.0000
   3.000   0.1650   0.04883   0.03896  -0.0293   0.8052   1.0000
   3.250   0.1931   0.04986   0.03994  -0.0313   0.7960   1.0000
   3.500   0.2068   0.05091   0.04094  -0.0317   0.7871   1.0000
   3.750   0.2518   0.05226   0.04224  -0.0357   0.7766   1.0000
   4.000   0.2526   0.05341   0.04338  -0.0348   0.7689   1.0000
   4.250   0.2904   0.05478   0.04471  -0.0377   0.7582   1.0000
   4.500   0.2984   0.05618   0.04610  -0.0375   0.7503   1.0000
   4.750   0.3299   0.05764   0.04754  -0.0396   0.7400   1.0000
   5.000   0.3435   0.05916   0.04906  -0.0400   0.7316   1.0000
   5.250   0.3672   0.06072   0.05062  -0.0412   0.7216   1.0000
   5.500   0.4076   0.06208   0.05201  -0.0437   0.7096   1.0000
   5.750   0.4032   0.06397   0.05390  -0.0425   0.7023   1.0000
   6.000   0.4341   0.06541   0.05535  -0.0439   0.6896   1.0000
   6.250   0.4480   0.06715   0.05712  -0.0441   0.6799   1.0000
   6.500   0.4633   0.06885   0.05887  -0.0443   0.6682   1.0000
   6.750   0.4902   0.07034   0.06041  -0.0452   0.6550   1.0000
   7.000   0.5232   0.07160   0.06172  -0.0463   0.6409   1.0000
   7.250   0.5316   0.07350   0.06367  -0.0459   0.6290   1.0000
   7.500   0.5449   0.07527   0.06550  -0.0458   0.6153   1.0000
   7.750   0.5640   0.07690   0.06720  -0.0459   0.6009   1.0000
   8.000   0.5860   0.07832   0.06869  -0.0460   0.5852   1.0000
   8.250   0.6080   0.07972   0.07018  -0.0460   0.5694   1.0000
   8.500   0.6298   0.08106   0.07162  -0.0459   0.5531   1.0000
   8.750   0.6512   0.08238   0.07304  -0.0457   0.5369   1.0000
   9.000   0.6711   0.08369   0.07445  -0.0453   0.5199   1.0000
   9.250   0.6905   0.08497   0.07584  -0.0448   0.5027   1.0000
   9.500   0.7100   0.08617   0.07714  -0.0443   0.4850   1.0000
   9.750   0.7314   0.08708   0.07817  -0.0435   0.4668   1.0000
  10.000   0.7560   0.08757   0.07881  -0.0426   0.4485   1.0000
  10.250   0.7915   0.08664   0.07804  -0.0412   0.4298   1.0000
  10.500   0.8461   0.08296   0.07459  -0.0388   0.4113   1.0000
  10.750   1.1335   0.04869   0.04094  -0.0321   0.3738   1.0000
  11.000   0.8656   0.08582   0.07765  -0.0363   0.3739   1.0000
  11.250   0.8770   0.08700   0.07895  -0.0351   0.3549   1.0000
  11.500   1.2107   0.04645   0.03805  -0.0259   0.2771   1.0000
  11.750   1.2189   0.04791   0.03935  -0.0238   0.2545   1.0000
  12.000   1.2367   0.04945   0.04068  -0.0225   0.2329   1.0000
  12.250   1.2447   0.05162   0.04281  -0.0209   0.2169   1.0000
  12.500   1.2594   0.05387   0.04500  -0.0199   0.2021   1.0000
  12.750   1.2794   0.05617   0.04721  -0.0194   0.1884   1.0000
  13.000   1.2608   0.05975   0.05117  -0.0167   0.1838   1.0000
  13.250   1.2843   0.06218   0.05354  -0.0165   0.1729   1.0000
  13.500   1.2594   0.06636   0.05808  -0.0142   0.1705   1.0000
  13.750   1.2340   0.07111   0.06312  -0.0128   0.1683   1.0000
  14.000   1.2032   0.07679   0.06908  -0.0122   0.1670   1.0000
  14.250   1.1498   0.08546   0.07807  -0.0134   0.1693   1.0000
  14.500   1.0892   0.09695   0.08976  -0.0172   0.1724   1.0000
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