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SG6050 (sg6050-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SG6050 (sg6050-il)
Reynolds number: 50,000
Max Cl/Cd: 8.21 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6050-il-50000.txt
Download as CSV file: xf-sg6050-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6050                                          
  
 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  -0.3396   0.11697   0.10995  -0.0303   1.0000   0.3487
  -9.750  -0.3110   0.11152   0.10444  -0.0302   1.0000   0.3565
  -9.500  -0.3338   0.11095   0.10401  -0.0291   1.0000   0.3647
  -9.250  -0.3223   0.10687   0.09995  -0.0285   1.0000   0.3689
  -9.000  -0.3213   0.10435   0.09748  -0.0270   1.0000   0.3732
  -8.750  -0.5981   0.08225   0.07630  -0.0405   1.0000   0.1920
  -8.500  -0.6194   0.07800   0.07205  -0.0390   1.0000   0.1898
  -8.250  -0.6414   0.07331   0.06734  -0.0378   1.0000   0.1881
  -8.000  -0.6656   0.06761   0.06151  -0.0375   1.0000   0.1861
  -7.750  -0.6852   0.06145   0.05506  -0.0376   1.0000   0.1853
  -7.500  -0.6940   0.05586   0.04901  -0.0378   1.0000   0.1867
  -7.250  -0.6944   0.05071   0.04320  -0.0382   1.0000   0.1898
  -7.000  -0.6816   0.04836   0.04073  -0.0373   1.0000   0.1954
  -6.750  -0.6674   0.04597   0.03805  -0.0369   1.0000   0.2012
  -6.500  -0.6519   0.04281   0.03422  -0.0373   1.0000   0.2076
  -6.250  -0.6333   0.04158   0.03304  -0.0365   1.0000   0.2143
  -6.000  -0.6133   0.03941   0.03026  -0.0368   1.0000   0.2223
  -5.750  -0.5939   0.03848   0.02944  -0.0360   1.0000   0.2307
  -5.500  -0.5723   0.03697   0.02759  -0.0361   1.0000   0.2399
  -5.250  -0.5514   0.03612   0.02666  -0.0357   1.0000   0.2515
  -5.000  -0.5307   0.03548   0.02603  -0.0352   1.0000   0.2651
  -4.750  -0.5094   0.03487   0.02540  -0.0348   1.0000   0.2813
  -4.500  -0.4881   0.03448   0.02502  -0.0343   1.0000   0.3030
  -4.250  -0.4675   0.03439   0.02501  -0.0336   1.0000   0.3334
  -4.000  -0.4481   0.03443   0.02524  -0.0325   1.0000   0.3725
  -3.750  -0.4285   0.03431   0.02525  -0.0313   1.0000   0.4301
  -3.500  -0.4108   0.03429   0.02539  -0.0296   1.0000   0.4812
  -3.250  -0.3943   0.03440   0.02561  -0.0277   1.0000   0.5211
  -3.000  -0.3773   0.03456   0.02580  -0.0260   1.0000   0.5555
  -2.750  -0.3599   0.03476   0.02600  -0.0246   1.0000   0.5874
  -2.500  -0.3435   0.03499   0.02628  -0.0229   1.0000   0.6165
  -2.250  -0.3151   0.03550   0.02679  -0.0232   0.9953   0.6505
  -2.000  -0.2812   0.03611   0.02741  -0.0245   0.9868   0.6877
  -1.750  -0.2508   0.03668   0.02799  -0.0250   0.9789   0.7217
  -1.500  -0.2177   0.03731   0.02861  -0.0261   0.9709   0.7525
  -1.250  -0.1942   0.03759   0.02890  -0.0261   0.9628   0.7778
  -1.000  -0.1625   0.03818   0.02945  -0.0274   0.9547   0.8069
  -0.750  -0.1407   0.03853   0.02984  -0.0269   0.9466   0.8382
  -0.500  -0.1129   0.03903   0.03038  -0.0273   0.9382   0.8827
  -0.250  -0.0555   0.03987   0.03120  -0.0344   0.9278   0.9590
   0.000  -0.0125   0.04005   0.03110  -0.0431   0.9170   1.0000
   0.250   0.0332   0.04109   0.03172  -0.0497   0.9071   1.0000
   0.500   0.0626   0.04202   0.03238  -0.0522   0.8973   1.0000
   0.750   0.0913   0.04310   0.03324  -0.0542   0.8878   1.0000
   1.000   0.1312   0.04432   0.03425  -0.0577   0.8776   1.0000
   1.250   0.1459   0.04529   0.03509  -0.0573   0.8680   1.0000
   1.500   0.1830   0.04655   0.03620  -0.0601   0.8577   1.0000
   1.750   0.2018   0.04762   0.03717  -0.0602   0.8478   1.0000
   2.000   0.2265   0.04885   0.03831  -0.0611   0.8378   1.0000
   2.250   0.2648   0.05011   0.03946  -0.0639   0.8272   1.0000
   2.500   0.2722   0.05133   0.04063  -0.0624   0.8176   1.0000
   2.750   0.3046   0.05262   0.04185  -0.0642   0.8069   1.0000
   3.000   0.3241   0.05390   0.04310  -0.0644   0.7967   1.0000
   3.250   0.3416   0.05529   0.04445  -0.0643   0.7864   1.0000
   3.500   0.3795   0.05655   0.04566  -0.0665   0.7752   1.0000
   3.750   0.3856   0.05804   0.04716  -0.0651   0.7653   1.0000
   4.000   0.4072   0.05946   0.04856  -0.0655   0.7542   1.0000
   4.250   0.4499   0.06063   0.04972  -0.0680   0.7431   1.0000
   4.500   0.4459   0.06242   0.05153  -0.0657   0.7330   1.0000
   4.750   0.4681   0.06391   0.05304  -0.0660   0.7220   1.0000
   5.000   0.5042   0.06513   0.05428  -0.0677   0.7112   1.0000
   5.250   0.5015   0.06716   0.05633  -0.0658   0.7009   1.0000
   5.500   0.5246   0.06870   0.05792  -0.0662   0.6901   1.0000
   5.750   0.5562   0.06997   0.05922  -0.0672   0.6790   1.0000
   6.000   0.5525   0.07228   0.06158  -0.0656   0.6690   1.0000
   6.250   0.5749   0.07388   0.06323  -0.0659   0.6579   1.0000
   6.500   0.6146   0.07482   0.06424  -0.0672   0.6461   1.0000
   6.750   0.6003   0.07776   0.06722  -0.0652   0.6366   1.0000
   7.000   0.6190   0.07946   0.06899  -0.0651   0.6248   1.0000
   7.250   0.6525   0.08058   0.07020  -0.0658   0.6127   1.0000
   7.500   0.6524   0.08310   0.07278  -0.0648   0.6018   1.0000
   7.750   0.6601   0.08540   0.07515  -0.0642   0.5906   1.0000
   8.000   0.6826   0.08696   0.07680  -0.0642   0.5782   1.0000
   8.250   0.7162   0.08782   0.07777  -0.0645   0.5653   1.0000
   8.500   0.7065   0.09119   0.08121  -0.0635   0.5546   1.0000
   8.750   0.7148   0.09354   0.08364  -0.0630   0.5424   1.0000
   9.000   0.7334   0.09534   0.08554  -0.0627   0.5299   1.0000
   9.250   0.7587   0.09651   0.08684  -0.0624   0.5162   1.0000
   9.500   0.7827   0.09774   0.08819  -0.0621   0.5031   1.0000
   9.750   0.7674   0.10197   0.09248  -0.0615   0.4915   1.0000
  10.000   0.7751   0.10455   0.09515  -0.0610   0.4789   1.0000
  10.250   0.7905   0.10647   0.09719  -0.0606   0.4655   1.0000
  10.500   0.8099   0.10796   0.09880  -0.0599   0.4515   1.0000
  10.750   0.8348   0.10885   0.09983  -0.0591   0.4375   1.0000
  11.000   0.8609   0.10932   0.10046  -0.0580   0.4230   1.0000
  11.250   0.8234   0.11684   0.10797  -0.0591   0.4136   1.0000
  11.500   0.8324   0.11937   0.11060  -0.0587   0.4004   1.0000
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