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NACA 0015 (naca0015-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 0015 (naca0015-il)
Reynolds number: 50,000
Max Cl/Cd: 24.7 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0015-il-50000.txt
Download as CSV file: xf-naca0015-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0015                                       
  
 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  -0.8022   0.07748   0.06925  -0.0308   1.0000   0.1885
 -10.750  -0.8442   0.07035   0.06203  -0.0311   1.0000   0.1873
 -10.500  -0.8851   0.06475   0.05627  -0.0287   1.0000   0.1865
 -10.250  -0.9176   0.05969   0.05093  -0.0257   1.0000   0.1869
 -10.000  -0.9434   0.05517   0.04599  -0.0220   1.0000   0.1883
  -9.750  -0.9165   0.05358   0.04459  -0.0216   1.0000   0.1959
  -9.500  -0.9248   0.05030   0.04100  -0.0185   1.0000   0.2010
  -9.250  -0.9332   0.04694   0.03723  -0.0150   1.0000   0.2061
  -9.000  -0.9132   0.04547   0.03586  -0.0138   1.0000   0.2161
  -8.750  -0.9076   0.04310   0.03330  -0.0112   1.0000   0.2249
  -8.500  -0.8997   0.04122   0.03122  -0.0086   1.0000   0.2360
  -8.250  -0.8818   0.03986   0.02996  -0.0070   1.0000   0.2489
  -8.000  -0.8680   0.03838   0.02847  -0.0048   1.0000   0.2627
  -7.750  -0.8545   0.03697   0.02703  -0.0026   1.0000   0.2778
  -7.500  -0.8402   0.03572   0.02578  -0.0003   1.0000   0.2944
  -7.250  -0.8248   0.03461   0.02471   0.0019   1.0000   0.3123
  -7.000  -0.8089   0.03359   0.02373   0.0041   1.0000   0.3315
  -6.750  -0.7934   0.03263   0.02281   0.0064   1.0000   0.3520
  -6.500  -0.7795   0.03164   0.02179   0.0089   1.0000   0.3737
  -6.250  -0.7622   0.03086   0.02112   0.0111   1.0000   0.3959
  -6.000  -0.7431   0.03032   0.02072   0.0132   1.0000   0.4189
  -5.750  -0.7273   0.02963   0.02006   0.0157   1.0000   0.4433
  -5.500  -0.7103   0.02904   0.01955   0.0180   1.0000   0.4678
  -5.250  -0.6910   0.02869   0.01933   0.0203   1.0000   0.4923
  -5.000  -0.6765   0.02808   0.01870   0.0229   1.0000   0.5187
  -4.750  -0.6558   0.02790   0.01869   0.0252   1.0000   0.5430
  -4.500  -0.6380   0.02761   0.01847   0.0278   1.0000   0.5688
  -4.250  -0.6209   0.02729   0.01819   0.0303   1.0000   0.5946
  -4.000  -0.6011   0.02725   0.01826   0.0329   1.0000   0.6194
  -3.750  -0.5860   0.02691   0.01792   0.0355   1.0000   0.6464
  -3.500  -0.5652   0.02701   0.01811   0.0381   1.0000   0.6703
  -3.250  -0.5463   0.02705   0.01819   0.0407   1.0000   0.6956
  -3.000  -0.5299   0.02694   0.01810   0.0433   1.0000   0.7219
  -2.750  -0.5069   0.02726   0.01845   0.0456   1.0000   0.7462
  -2.500  -0.4886   0.02733   0.01852   0.0480   1.0000   0.7732
  -2.250  -0.4624   0.02772   0.01892   0.0494   1.0000   0.7982
  -2.000  -0.4322   0.02817   0.01934   0.0500   1.0000   0.8243
  -1.750  -0.3985   0.02859   0.01972   0.0494   1.0000   0.8513
  -1.500  -0.3429   0.02935   0.02041   0.0451   1.0000   0.8763
  -1.250  -0.2907   0.02981   0.02081   0.0404   1.0000   0.9034
  -1.000  -0.2043   0.03039   0.02129   0.0292   1.0000   0.9258
  -0.750  -0.1382   0.03057   0.02142   0.0206   1.0000   0.9519
  -0.500  -0.0601   0.03056   0.02139   0.0091   1.0000   0.9754
  -0.250   0.0230   0.03035   0.02116  -0.0040   1.0000   0.9999
   0.000   0.0000   0.03036   0.02118   0.0000   1.0000   1.0000
   0.250  -0.0230   0.03035   0.02116   0.0040   0.9999   1.0000
   0.500   0.0600   0.03056   0.02138  -0.0091   0.9754   1.0000
   0.750   0.1382   0.03056   0.02141  -0.0206   0.9519   1.0000
   1.000   0.2042   0.03039   0.02129  -0.0291   0.9258   1.0000
   1.250   0.2906   0.02981   0.02080  -0.0403   0.9034   1.0000
   1.500   0.3428   0.02934   0.02041  -0.0451   0.8763   1.0000
   1.750   0.3983   0.02858   0.01972  -0.0494   0.8513   1.0000
   2.000   0.4321   0.02816   0.01933  -0.0499   0.8244   1.0000
   2.250   0.4623   0.02771   0.01891  -0.0494   0.7982   1.0000
   2.500   0.4886   0.02733   0.01852  -0.0480   0.7732   1.0000
   2.750   0.5068   0.02726   0.01845  -0.0456   0.7462   1.0000
   3.000   0.5298   0.02694   0.01810  -0.0433   0.7220   1.0000
   3.250   0.5462   0.02704   0.01818  -0.0407   0.6957   1.0000
   3.500   0.5651   0.02701   0.01810  -0.0381   0.6703   1.0000
   3.750   0.5859   0.02691   0.01791  -0.0355   0.6464   1.0000
   4.000   0.6009   0.02725   0.01825  -0.0328   0.6194   1.0000
   4.250   0.6208   0.02729   0.01819  -0.0303   0.5946   1.0000
   4.500   0.6379   0.02760   0.01847  -0.0277   0.5689   1.0000
   4.750   0.6556   0.02790   0.01869  -0.0252   0.5431   1.0000
   5.000   0.6764   0.02807   0.01870  -0.0229   0.5187   1.0000
   5.250   0.6909   0.02869   0.01933  -0.0203   0.4924   1.0000
   5.500   0.7102   0.02904   0.01955  -0.0180   0.4678   1.0000
   5.750   0.7272   0.02962   0.02006  -0.0157   0.4434   1.0000
   6.000   0.7430   0.03031   0.02071  -0.0132   0.4190   1.0000
   6.250   0.7621   0.03086   0.02112  -0.0111   0.3959   1.0000
   6.500   0.7795   0.03163   0.02178  -0.0089   0.3738   1.0000
   6.750   0.7934   0.03263   0.02280  -0.0064   0.3520   1.0000
   7.000   0.8088   0.03359   0.02373  -0.0041   0.3315   1.0000
   7.250   0.8247   0.03460   0.02470  -0.0019   0.3123   1.0000
   7.500   0.8401   0.03572   0.02578   0.0003   0.2944   1.0000
   7.750   0.8544   0.03697   0.02703   0.0026   0.2778   1.0000
   8.000   0.8680   0.03838   0.02846   0.0048   0.2627   1.0000
   8.250   0.8818   0.03986   0.02996   0.0070   0.2489   1.0000
   8.500   0.8996   0.04122   0.03121   0.0086   0.2360   1.0000
   8.750   0.9077   0.04310   0.03329   0.0112   0.2249   1.0000
   9.000   0.9132   0.04547   0.03586   0.0138   0.2160   1.0000
   9.250   0.9334   0.04694   0.03723   0.0150   0.2061   1.0000
   9.500   0.9249   0.05030   0.04100   0.0185   0.2010   1.0000
   9.750   0.9167   0.05358   0.04459   0.0216   0.1959   1.0000
  10.000   0.9434   0.05519   0.04600   0.0220   0.1883   1.0000
  10.250   0.9177   0.05971   0.05095   0.0256   0.1869   1.0000
  10.500   0.8853   0.06478   0.05630   0.0286   0.1865   1.0000
  10.750   0.8443   0.07039   0.06208   0.0310   0.1873   1.0000
  11.000   0.8024   0.07755   0.06932   0.0307   0.1885   1.0000
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