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Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 50,000
Max Cl/Cd: 29.91 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-curtisc72-il-50000.txt
Download as CSV file: xf-curtisc72-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Curtis C-72                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3379   0.11216   0.10500  -0.0267   1.0000   0.2526
 -10.750  -0.3209   0.10827   0.10109  -0.0255   1.0000   0.2623
 -10.500  -0.3342   0.10692   0.09989  -0.0255   1.0000   0.2690
 -10.250  -0.3213   0.10362   0.09660  -0.0241   1.0000   0.2800
 -10.000  -0.3204   0.10094   0.09401  -0.0230   1.0000   0.2884
  -9.750  -0.3397   0.10079   0.09402  -0.0213   1.0000   0.2989
  -9.500  -0.3209   0.09670   0.08994  -0.0196   1.0000   0.3110
  -9.250  -0.3301   0.09497   0.08834  -0.0175   1.0000   0.3200
  -9.000  -0.3488   0.09462   0.08814  -0.0141   1.0000   0.3310
  -8.750  -0.3352   0.09105   0.08460  -0.0123   1.0000   0.3412
  -8.500  -0.3874   0.09309   0.08690  -0.0067   1.0000   0.3484
  -8.250  -0.3643   0.08889   0.08269  -0.0048   1.0000   0.3615
  -8.000  -0.3709   0.08690   0.08079  -0.0016   1.0000   0.3707
  -7.750  -0.4007   0.08673   0.08081   0.0019   1.0000   0.3824
  -7.500  -0.4098   0.08538   0.07954   0.0049   1.0000   0.3969
  -7.250  -0.3968   0.08206   0.07623   0.0079   1.0000   0.4083
  -7.000  -0.4023   0.08012   0.07437   0.0108   1.0000   0.4219
  -6.750  -0.3972   0.05538   0.04830  -0.0444   1.0000   0.1863
  -6.500  -0.3754   0.05004   0.04270  -0.0471   1.0000   0.1729
  -6.250  -0.3496   0.04602   0.03820  -0.0500   1.0000   0.1674
  -6.000  -0.3236   0.04268   0.03446  -0.0522   1.0000   0.1651
  -5.750  -0.2948   0.03951   0.03074  -0.0543   1.0000   0.1620
  -5.500  -0.2664   0.03705   0.02776  -0.0558   1.0000   0.1610
  -5.250  -0.2394   0.03522   0.02554  -0.0566   1.0000   0.1625
  -5.000  -0.2129   0.03387   0.02378  -0.0571   1.0000   0.1677
  -4.750  -0.1874   0.03264   0.02230  -0.0575   1.0000   0.1738
  -4.500  -0.1626   0.03170   0.02123  -0.0575   1.0000   0.1809
  -4.250  -0.1374   0.03082   0.02020  -0.0576   1.0000   0.1906
  -4.000  -0.1129   0.03016   0.01956  -0.0576   1.0000   0.2086
  -3.750  -0.0870   0.02947   0.01893  -0.0578   1.0000   0.2383
  -3.500  -0.0573   0.02866   0.01854  -0.0586   1.0000   0.3117
  -3.250  -0.0309   0.02777   0.01914  -0.0577   1.0000   0.5620
  -3.000  -0.0188   0.02713   0.01926  -0.0531   1.0000   0.7378
  -2.750  -0.0259   0.02627   0.01901  -0.0467   1.0000   1.0000
  -2.500   0.0190   0.02729   0.01935  -0.0523   0.9950   1.0000
  -2.250   0.0775   0.02861   0.02011  -0.0597   0.9804   1.0000
  -2.000   0.1283   0.02972   0.02084  -0.0653   0.9644   1.0000
  -1.750   0.1768   0.03075   0.02154  -0.0703   0.9482   1.0000
  -1.500   0.2232   0.03169   0.02223  -0.0746   0.9319   1.0000
  -1.250   0.2669   0.03255   0.02288  -0.0783   0.9158   1.0000
  -1.000   0.3083   0.03335   0.02350  -0.0814   0.8995   1.0000
  -0.750   0.3479   0.03409   0.02411  -0.0841   0.8833   1.0000
  -0.500   0.3865   0.03477   0.02468  -0.0864   0.8669   1.0000
  -0.250   0.4246   0.03539   0.02521  -0.0885   0.8503   1.0000
   0.000   0.4618   0.03595   0.02571  -0.0902   0.8339   1.0000
   0.250   0.4992   0.03642   0.02613  -0.0918   0.8174   1.0000
   0.500   0.5360   0.03682   0.02650  -0.0932   0.8010   1.0000
   0.750   0.5720   0.03717   0.02683  -0.0943   0.7847   1.0000
   1.000   0.6080   0.03741   0.02707  -0.0951   0.7686   1.0000
   1.250   0.6427   0.03763   0.02730  -0.0957   0.7526   1.0000
   1.500   0.6765   0.03783   0.02753  -0.0961   0.7369   1.0000
   1.750   0.7080   0.03805   0.02777  -0.0961   0.7213   1.0000
   2.000   0.7370   0.03838   0.02814  -0.0958   0.7058   1.0000
   2.250   0.7646   0.03877   0.02857  -0.0953   0.6906   1.0000
   2.500   0.7905   0.03929   0.02912  -0.0946   0.6756   1.0000
   2.750   0.8149   0.03994   0.02983  -0.0939   0.6609   1.0000
   3.000   0.8392   0.04059   0.03053  -0.0932   0.6468   1.0000
   3.250   0.8656   0.04112   0.03113  -0.0926   0.6338   1.0000
   3.500   0.9141   0.03985   0.02995  -0.0932   0.6244   1.0000
   3.750   0.9306   0.04108   0.03125  -0.0919   0.6098   1.0000
   4.000   0.9465   0.04237   0.03262  -0.0906   0.5955   1.0000
   4.250   0.9629   0.04363   0.03397  -0.0893   0.5816   1.0000
   4.500   0.9840   0.04448   0.03492  -0.0882   0.5684   1.0000
   4.750   1.0190   0.04406   0.03460  -0.0877   0.5562   1.0000
   5.000   1.0726   0.04194   0.03257  -0.0880   0.5441   1.0000
   5.250   1.0988   0.04208   0.03281  -0.0868   0.5291   1.0000
   5.500   1.1268   0.04201   0.03283  -0.0857   0.5133   1.0000
   5.750   1.1604   0.04144   0.03232  -0.0849   0.4969   1.0000
   6.000   1.1801   0.04202   0.03302  -0.0832   0.4798   1.0000
   6.250   1.1993   0.04267   0.03378  -0.0815   0.4625   1.0000
   6.500   1.2190   0.04330   0.03452  -0.0799   0.4445   1.0000
   6.750   1.2415   0.04374   0.03508  -0.0784   0.4260   1.0000
   7.000   1.2720   0.04364   0.03500  -0.0774   0.4061   1.0000
   7.250   1.3048   0.04362   0.03491  -0.0768   0.3856   1.0000
   7.500   1.3136   0.04526   0.03672  -0.0743   0.3668   1.0000
   7.750   1.3270   0.04665   0.03823  -0.0722   0.3478   1.0000
   8.000   1.3449   0.04784   0.03947  -0.0705   0.3289   1.0000
   8.250   1.3780   0.04799   0.03944  -0.0701   0.3074   1.0000
   8.500   1.3843   0.04963   0.04122  -0.0674   0.2905   1.0000
   8.750   1.3894   0.05100   0.04273  -0.0646   0.2734   1.0000
   9.000   1.3944   0.05214   0.04395  -0.0618   0.2562   1.0000
   9.250   1.3995   0.05311   0.04496  -0.0589   0.2392   1.0000
   9.500   1.4047   0.05393   0.04578  -0.0561   0.2222   1.0000
   9.750   1.4222   0.05381   0.04535  -0.0542   0.2012   1.0000
  10.000   1.4192   0.05542   0.04695  -0.0508   0.1867   1.0000
  10.250   1.4170   0.05735   0.04886  -0.0477   0.1727   1.0000
  10.500   1.3914   0.06112   0.05303  -0.0438   0.1674   1.0000
  10.750   1.3894   0.06375   0.05563  -0.0416   0.1559   1.0000
  11.000   1.3942   0.06630   0.05807  -0.0399   0.1443   1.0000
  11.250   1.3651   0.07120   0.06335  -0.0377   0.1425   1.0000
  11.500   1.3342   0.07693   0.06940  -0.0367   0.1415   1.0000
  11.750   1.2983   0.08394   0.07670  -0.0371   0.1420   1.0000
  12.000   1.2586   0.09246   0.08542  -0.0390   0.1436   1.0000
  12.250   1.2186   0.10230   0.09541  -0.0424   0.1452   1.0000
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