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SG6041 (sg6041-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SG6041 (sg6041-il)
Reynolds number: 50,000
Max Cl/Cd: 35.08 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6041-il-50000-n5.txt
Download as CSV file: xf-sg6041-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6041                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4495   0.09485   0.08768  -0.0421   1.0000   0.0455
  -9.000  -0.4522   0.09096   0.08387  -0.0430   1.0000   0.0453
  -8.750  -0.4583   0.08688   0.07987  -0.0444   1.0000   0.0451
  -8.500  -0.4648   0.08333   0.07640  -0.0449   1.0000   0.0446
  -8.250  -0.4765   0.07999   0.07315  -0.0448   1.0000   0.0442
  -8.000  -0.4868   0.07666   0.06987  -0.0442   1.0000   0.0437
  -7.750  -0.4978   0.07316   0.06639  -0.0436   1.0000   0.0434
  -7.500  -0.5076   0.06976   0.06296  -0.0426   1.0000   0.0431
  -7.250  -0.5158   0.06633   0.05947  -0.0414   1.0000   0.0428
  -7.000  -0.5218   0.06289   0.05592  -0.0400   1.0000   0.0425
  -6.750  -0.5252   0.05944   0.05230  -0.0384   1.0000   0.0422
  -6.500  -0.5259   0.05590   0.04854  -0.0369   1.0000   0.0418
  -6.250  -0.5238   0.05230   0.04465  -0.0353   1.0000   0.0416
  -6.000  -0.5181   0.04888   0.04089  -0.0338   1.0000   0.0415
  -5.750  -0.5092   0.04560   0.03721  -0.0323   1.0000   0.0416
  -5.500  -0.4975   0.04242   0.03359  -0.0308   1.0000   0.0420
  -5.250  -0.4829   0.03957   0.03027  -0.0293   1.0000   0.0430
  -5.000  -0.4656   0.03691   0.02698  -0.0279   1.0000   0.0452
  -4.750  -0.4480   0.03475   0.02459  -0.0268   1.0000   0.0478
  -4.500  -0.4285   0.03291   0.02251  -0.0256   1.0000   0.0502
  -4.250  -0.4071   0.03111   0.02036  -0.0244   1.0000   0.0536
  -4.000  -0.3851   0.02953   0.01843  -0.0231   1.0000   0.0586
  -3.750  -0.3636   0.02821   0.01704  -0.0220   1.0000   0.0641
  -3.500  -0.3414   0.02701   0.01566  -0.0207   1.0000   0.0726
  -3.250  -0.3199   0.02604   0.01453  -0.0193   1.0000   0.0834
  -3.000  -0.2988   0.02508   0.01356  -0.0182   1.0000   0.0992
  -2.750  -0.2779   0.02417   0.01268  -0.0173   1.0000   0.1214
  -2.500  -0.2573   0.02325   0.01186  -0.0164   1.0000   0.1565
  -2.250  -0.2368   0.02191   0.01113  -0.0159   1.0000   0.2435
  -2.000  -0.2289   0.02001   0.01133  -0.0116   1.0000   0.6368
  -1.750  -0.2082   0.02005   0.01165  -0.0080   0.9947   0.8321
  -1.500  -0.1231   0.02035   0.01165  -0.0172   0.9961   1.0000
  -1.250  -0.0891   0.02054   0.01149  -0.0196   0.9879   1.0000
  -1.000  -0.0557   0.02076   0.01139  -0.0217   0.9798   1.0000
  -0.750  -0.0199   0.02105   0.01141  -0.0242   0.9720   1.0000
  -0.500   0.0113   0.02125   0.01136  -0.0257   0.9627   1.0000
  -0.250   0.0457   0.02152   0.01143  -0.0277   0.9541   1.0000
   0.000   0.0810   0.02180   0.01152  -0.0299   0.9452   1.0000
   0.250   0.1124   0.02202   0.01159  -0.0312   0.9350   1.0000
   0.500   0.1481   0.02228   0.01173  -0.0332   0.9259   1.0000
   0.750   0.1835   0.02251   0.01187  -0.0351   0.9159   1.0000
   1.000   0.2145   0.02272   0.01199  -0.0361   0.9045   1.0000
   1.250   0.2485   0.02291   0.01213  -0.0375   0.8935   1.0000
   1.500   0.2896   0.02305   0.01225  -0.0402   0.8840   1.0000
   1.750   0.3212   0.02316   0.01235  -0.0410   0.8710   1.0000
   2.000   0.3531   0.02324   0.01244  -0.0417   0.8577   1.0000
   2.250   0.3863   0.02327   0.01249  -0.0426   0.8441   1.0000
   2.500   0.4203   0.02322   0.01250  -0.0434   0.8299   1.0000
   2.750   0.4541   0.02312   0.01246  -0.0440   0.8149   1.0000
   3.000   0.4870   0.02295   0.01236  -0.0443   0.7989   1.0000
   3.250   0.5202   0.02270   0.01222  -0.0445   0.7820   1.0000
   3.500   0.5496   0.02247   0.01207  -0.0440   0.7625   1.0000
   3.750   0.5779   0.02222   0.01191  -0.0431   0.7406   1.0000
   4.000   0.6076   0.02191   0.01172  -0.0424   0.7171   1.0000
   4.250   0.6382   0.02159   0.01147  -0.0418   0.6908   1.0000
   4.500   0.6655   0.02141   0.01134  -0.0406   0.6590   1.0000
   4.750   0.6935   0.02127   0.01123  -0.0396   0.6224   1.0000
   5.000   0.7205   0.02126   0.01116  -0.0384   0.5803   1.0000
   5.250   0.7450   0.02144   0.01120  -0.0370   0.5334   1.0000
   5.500   0.7666   0.02185   0.01144  -0.0353   0.4848   1.0000
   5.750   0.7854   0.02245   0.01183  -0.0334   0.4369   1.0000
   6.000   0.8026   0.02320   0.01236  -0.0315   0.3922   1.0000
   6.250   0.8191   0.02404   0.01302  -0.0296   0.3511   1.0000
   6.500   0.8357   0.02496   0.01378  -0.0279   0.3150   1.0000
   6.750   0.8524   0.02592   0.01464  -0.0263   0.2829   1.0000
   7.000   0.8698   0.02694   0.01555  -0.0249   0.2557   1.0000
   7.250   0.8876   0.02798   0.01652  -0.0236   0.2320   1.0000
   7.500   0.9071   0.02906   0.01759  -0.0226   0.2113   1.0000
   7.750   0.9266   0.03017   0.01874  -0.0216   0.1926   1.0000
   8.000   0.9470   0.03134   0.01994  -0.0207   0.1770   1.0000
   8.250   0.9680   0.03258   0.02124  -0.0199   0.1634   1.0000
   8.500   0.9879   0.03385   0.02259  -0.0190   0.1506   1.0000
   8.750   1.0093   0.03526   0.02411  -0.0183   0.1403   1.0000
   9.000   1.0291   0.03666   0.02552  -0.0175   0.1308   1.0000
   9.250   1.0470   0.03821   0.02735  -0.0164   0.1212   1.0000
   9.500   1.0662   0.03991   0.02917  -0.0156   0.1138   1.0000
   9.750   1.0813   0.04154   0.03100  -0.0143   0.1062   1.0000
  10.000   1.0963   0.04347   0.03317  -0.0131   0.0998   1.0000
  10.250   1.1086   0.04545   0.03542  -0.0116   0.0940   1.0000
  10.500   1.1216   0.04731   0.03732  -0.0104   0.0890   1.0000
  10.750   1.1256   0.04999   0.04049  -0.0082   0.0847   1.0000
  11.000   1.1304   0.05240   0.04316  -0.0062   0.0813   1.0000
  11.250   1.1400   0.05431   0.04508  -0.0048   0.0779   1.0000
  11.500   1.1320   0.05740   0.04854  -0.0021   0.0757   1.0000
  11.750   1.1184   0.06084   0.05237   0.0005   0.0739   1.0000
  12.000   1.1035   0.06453   0.05638   0.0023   0.0724   1.0000
  12.250   1.0860   0.06869   0.06080   0.0033   0.0714   1.0000
  12.500   1.0641   0.07361   0.06597   0.0033   0.0708   1.0000
  12.750   1.0351   0.07990   0.07250   0.0016   0.0709   1.0000
  13.000   0.9952   0.08884   0.08163  -0.0028   0.0719   1.0000
  13.250   0.9492   0.10119   0.09408  -0.0105   0.0738   1.0000
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