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SG6051 (sg6051-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 50,000
Max Cl/Cd: 34.3 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6051-il-50000-n5.txt
Download as CSV file: xf-sg6051-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6051                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4050   0.10352   0.09659  -0.0462   1.0000   0.0506
  -9.500  -0.4084   0.09936   0.09252  -0.0479   1.0000   0.0506
  -9.250  -0.4142   0.09526   0.08852  -0.0494   1.0000   0.0507
  -9.000  -0.4235   0.09139   0.08476  -0.0504   1.0000   0.0506
  -8.750  -0.4381   0.08801   0.08152  -0.0503   1.0000   0.0503
  -8.500  -0.4583   0.08514   0.07878  -0.0492   1.0000   0.0498
  -8.250  -0.4783   0.08182   0.07556  -0.0486   1.0000   0.0492
  -8.000  -0.4969   0.07827   0.07205  -0.0479   1.0000   0.0487
  -7.750  -0.5136   0.07459   0.06836  -0.0471   1.0000   0.0484
  -7.500  -0.5270   0.07069   0.06439  -0.0465   1.0000   0.0483
  -7.250  -0.5364   0.06662   0.06017  -0.0461   1.0000   0.0487
  -7.000  -0.5413   0.06237   0.05569  -0.0459   1.0000   0.0493
  -6.750  -0.5277   0.05623   0.04900  -0.0495   0.9952   0.0507
  -6.500  -0.5077   0.05029   0.04227  -0.0527   0.9897   0.0526
  -6.250  -0.4826   0.04675   0.03838  -0.0551   0.9851   0.0566
  -6.000  -0.4565   0.04364   0.03482  -0.0568   0.9802   0.0607
  -5.750  -0.4272   0.04012   0.03035  -0.0585   0.9755   0.0666
  -5.500  -0.3963   0.03791   0.02797  -0.0603   0.9719   0.0718
  -5.250  -0.3673   0.03590   0.02534  -0.0611   0.9668   0.0785
  -5.000  -0.3365   0.03410   0.02333  -0.0624   0.9624   0.0841
  -4.750  -0.3021   0.03270   0.02155  -0.0639   0.9588   0.0919
  -4.500  -0.2729   0.03143   0.02012  -0.0645   0.9540   0.0978
  -4.250  -0.2420   0.03053   0.01895  -0.0653   0.9491   0.1073
  -4.000  -0.2086   0.02953   0.01791  -0.0667   0.9453   0.1156
  -3.750  -0.1768   0.02878   0.01706  -0.0679   0.9409   0.1293
  -3.500  -0.1481   0.02808   0.01627  -0.0685   0.9353   0.1456
  -3.250  -0.1141   0.02725   0.01550  -0.0703   0.9312   0.1771
  -3.000  -0.0790   0.02592   0.01495  -0.0727   0.9282   0.2900
  -2.750  -0.0579   0.02531   0.01494  -0.0718   0.9215   0.4720
  -2.500  -0.0315   0.02481   0.01495  -0.0711   0.9169   0.6023
  -2.250  -0.0050   0.02441   0.01506  -0.0693   0.9135   0.7513
  -2.000   0.0497   0.02436   0.01513  -0.0732   0.9091   1.0000
  -1.750   0.0783   0.02451   0.01492  -0.0743   0.9028   1.0000
  -1.500   0.1155   0.02465   0.01470  -0.0768   0.8986   1.0000
  -1.250   0.1343   0.02497   0.01476  -0.0759   0.8901   1.0000
  -1.000   0.1684   0.02517   0.01470  -0.0776   0.8854   1.0000
  -0.750   0.1915   0.02550   0.01483  -0.0774   0.8780   1.0000
  -0.500   0.2211   0.02578   0.01490  -0.0783   0.8721   1.0000
  -0.250   0.2526   0.02604   0.01498  -0.0794   0.8669   1.0000
   0.000   0.2741   0.02645   0.01526  -0.0788   0.8589   1.0000
   0.250   0.3086   0.02667   0.01533  -0.0804   0.8544   1.0000
   0.500   0.3276   0.02716   0.01572  -0.0793   0.8457   1.0000
   0.750   0.3599   0.02741   0.01587  -0.0805   0.8405   1.0000
   1.000   0.3814   0.02788   0.01628  -0.0798   0.8324   1.0000
   1.250   0.4113   0.02818   0.01651  -0.0805   0.8264   1.0000
   1.500   0.4351   0.02862   0.01692  -0.0802   0.8189   1.0000
   1.750   0.4625   0.02898   0.01724  -0.0805   0.8120   1.0000
   2.000   0.4881   0.02939   0.01765  -0.0805   0.8050   1.0000
   2.250   0.5134   0.02979   0.01805  -0.0804   0.7974   1.0000
   2.500   0.5392   0.03020   0.01847  -0.0803   0.7902   1.0000
   2.750   0.5647   0.03059   0.01890  -0.0802   0.7823   1.0000
   3.000   0.5878   0.03106   0.01941  -0.0797   0.7739   1.0000
   3.250   0.6167   0.03130   0.01971  -0.0799   0.7668   1.0000
   3.500   0.6371   0.03185   0.02031  -0.0790   0.7569   1.0000
   3.750   0.6704   0.03186   0.02044  -0.0797   0.7508   1.0000
   4.000   0.6889   0.03245   0.02111  -0.0785   0.7396   1.0000
   4.250   0.7152   0.03270   0.02146  -0.0782   0.7309   1.0000
   4.500   0.7439   0.03277   0.02168  -0.0780   0.7223   1.0000
   4.750   0.7642   0.03321   0.02224  -0.0769   0.7106   1.0000
   5.000   0.7898   0.03334   0.02251  -0.0762   0.7003   1.0000
   5.250   0.8235   0.03297   0.02234  -0.0764   0.6917   1.0000
   5.500   0.8448   0.03319   0.02271  -0.0751   0.6787   1.0000
   5.750   0.8680   0.03324   0.02294  -0.0739   0.6655   1.0000
   6.000   0.8928   0.03312   0.02300  -0.0727   0.6518   1.0000
   6.250   0.9187   0.03284   0.02295  -0.0715   0.6374   1.0000
   6.500   0.9454   0.03242   0.02273  -0.0702   0.6216   1.0000
   6.750   0.9739   0.03176   0.02227  -0.0690   0.6043   1.0000
   7.000   0.9917   0.03171   0.02244  -0.0666   0.5820   1.0000
   7.250   1.0166   0.03111   0.02201  -0.0647   0.5576   1.0000
   7.500   1.0344   0.03096   0.02200  -0.0622   0.5272   1.0000
   7.750   1.0503   0.03094   0.02205  -0.0594   0.4900   1.0000
   8.000   1.0646   0.03104   0.02212  -0.0563   0.4458   1.0000
   8.250   1.0749   0.03158   0.02246  -0.0530   0.3948   1.0000
   8.500   1.0796   0.03271   0.02331  -0.0496   0.3419   1.0000
   8.750   1.0802   0.03436   0.02465  -0.0462   0.2929   1.0000
   9.000   1.0792   0.03635   0.02637  -0.0432   0.2496   1.0000
   9.250   1.0780   0.03855   0.02834  -0.0406   0.2116   1.0000
   9.500   1.0776   0.04086   0.03045  -0.0383   0.1810   1.0000
   9.750   1.0789   0.04317   0.03267  -0.0362   0.1559   1.0000
  10.000   1.0805   0.04554   0.03488  -0.0343   0.1372   1.0000
  10.250   1.0852   0.04776   0.03709  -0.0327   0.1210   1.0000
  10.500   1.0910   0.04994   0.03925  -0.0311   0.1086   1.0000
  10.750   1.0994   0.05199   0.04132  -0.0295   0.0984   1.0000
  11.000   1.1105   0.05392   0.04339  -0.0281   0.0886   1.0000
  11.250   1.1245   0.05575   0.04529  -0.0267   0.0811   1.0000
  11.500   1.1390   0.05761   0.04731  -0.0255   0.0742   1.0000
  11.750   1.1544   0.05966   0.04954  -0.0243   0.0680   1.0000
  12.000   1.1677   0.06188   0.05194  -0.0232   0.0630   1.0000
  12.250   1.1801   0.06428   0.05441  -0.0222   0.0588   1.0000
  12.500   1.1858   0.06739   0.05794  -0.0210   0.0553   1.0000
  12.750   1.1896   0.07051   0.06132  -0.0200   0.0526   1.0000
  13.000   1.1922   0.07345   0.06436  -0.0193   0.0502   1.0000
  13.250   1.1914   0.07712   0.06821  -0.0186   0.0483   1.0000
  13.500   1.1797   0.08178   0.07329  -0.0182   0.0472   1.0000
  13.750   1.1659   0.08684   0.07870  -0.0184   0.0465   1.0000
  14.000   1.1496   0.09240   0.08458  -0.0191   0.0460   1.0000
  14.250   1.1304   0.09855   0.09101  -0.0207   0.0458   1.0000
  14.500   1.1087   0.10546   0.09818  -0.0233   0.0458   1.0000
  14.750   1.0849   0.11337   0.10633  -0.0271   0.0460   1.0000
  15.000   1.0594   0.12253   0.11567  -0.0323   0.0464   1.0000
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