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NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(2)-415 (naca642415-il)
Reynolds number: 50,000
Max Cl/Cd: 25.86 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca642415-il-50000-n5.txt
Download as CSV file: xf-naca642415-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-415                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4597   0.10524   0.09757  -0.0519   1.0000   0.0649
 -11.750  -0.4685   0.09871   0.09109  -0.0552   1.0000   0.0645
 -11.500  -0.4840   0.09116   0.08357  -0.0596   1.0000   0.0639
 -11.250  -0.5093   0.08321   0.07564  -0.0645   1.0000   0.0633
 -11.000  -0.5391   0.07622   0.06863  -0.0686   1.0000   0.0625
 -10.750  -0.5681   0.07078   0.06313  -0.0708   1.0000   0.0619
 -10.500  -0.5959   0.06674   0.05903  -0.0709   1.0000   0.0617
 -10.250  -0.6239   0.06384   0.05608  -0.0689   1.0000   0.0614
 -10.000  -0.6486   0.06148   0.05367  -0.0657   1.0000   0.0614
  -9.750  -0.6689   0.05928   0.05136  -0.0623   1.0000   0.0615
  -9.500  -0.6866   0.05727   0.04922  -0.0587   1.0000   0.0618
  -9.250  -0.7012   0.05531   0.04709  -0.0550   1.0000   0.0624
  -9.000  -0.7122   0.05333   0.04490  -0.0516   1.0000   0.0631
  -8.750  -0.7194   0.05127   0.04258  -0.0485   1.0000   0.0639
  -8.500  -0.7201   0.04896   0.03992  -0.0464   0.9990   0.0650
  -8.250  -0.6956   0.04570   0.03604  -0.0485   0.9906   0.0664
  -8.000  -0.6660   0.04304   0.03313  -0.0506   0.9838   0.0680
  -7.750  -0.6367   0.04116   0.03111  -0.0523   0.9761   0.0709
  -7.500  -0.6061   0.03933   0.02901  -0.0538   0.9689   0.0746
  -7.250  -0.5728   0.03756   0.02684  -0.0552   0.9622   0.0778
  -7.000  -0.5404   0.03609   0.02539  -0.0563   0.9557   0.0815
  -6.750  -0.5076   0.03495   0.02414  -0.0575   0.9488   0.0873
  -6.500  -0.4723   0.03383   0.02290  -0.0586   0.9433   0.0929
  -6.250  -0.4451   0.03289   0.02194  -0.0589   0.9349   0.1001
  -6.000  -0.4114   0.03179   0.02081  -0.0605   0.9293   0.1100
  -5.750  -0.3906   0.03089   0.01987  -0.0601   0.9197   0.1210
  -5.500  -0.3613   0.02957   0.01867  -0.0617   0.9134   0.1408
  -5.250  -0.3444   0.02833   0.01763  -0.0613   0.9034   0.1702
  -5.000  -0.3229   0.02614   0.01631  -0.0628   0.8967   0.2744
  -4.750  -0.3118   0.02583   0.01711  -0.0593   0.8869   0.4607
  -4.500  -0.2826   0.02634   0.01753  -0.0587   0.8805   0.5438
  -4.250  -0.2639   0.02704   0.01813  -0.0560   0.8713   0.5852
  -4.000  -0.2380   0.02787   0.01885  -0.0540   0.8648   0.6243
  -3.750  -0.2189   0.02901   0.01994  -0.0499   0.8570   0.6541
  -3.500  -0.1968   0.02976   0.02059  -0.0470   0.8498   0.6788
  -3.250  -0.1654   0.03007   0.02072  -0.0463   0.8452   0.6963
  -3.000  -0.1511   0.03012   0.02063  -0.0442   0.8354   0.7079
  -2.750  -0.1205   0.03004   0.02037  -0.0444   0.8302   0.7162
  -2.500  -0.1014   0.02991   0.02009  -0.0437   0.8221   0.7259
  -2.250  -0.0758   0.02986   0.01989  -0.0433   0.8157   0.7328
  -2.000  -0.0437   0.02964   0.01950  -0.0443   0.8114   0.7411
  -1.750  -0.0301   0.02971   0.01950  -0.0425   0.8021   0.7484
  -1.500  -0.0015   0.02959   0.01925  -0.0429   0.7969   0.7555
  -1.250   0.0221   0.02952   0.01906  -0.0429   0.7910   0.7631
  -1.000   0.0412   0.02961   0.01910  -0.0419   0.7836   0.7693
  -0.750   0.0709   0.02947   0.01883  -0.0428   0.7791   0.7771
  -0.500   0.0888   0.02962   0.01894  -0.0416   0.7720   0.7834
  -0.250   0.1110   0.02969   0.01896  -0.0413   0.7658   0.7909
   0.000   0.1408   0.02964   0.01883  -0.0420   0.7619   0.7978
   0.250   0.1554   0.02995   0.01913  -0.0406   0.7547   0.8054
   0.500   0.1780   0.03008   0.01923  -0.0404   0.7488   0.8137
   0.750   0.2073   0.03008   0.01920  -0.0407   0.7451   0.8210
   1.000   0.2203   0.03051   0.01963  -0.0393   0.7377   0.8302
   1.250   0.2413   0.03076   0.01989  -0.0387   0.7323   0.8388
   1.500   0.2702   0.03081   0.01994  -0.0391   0.7287   0.8477
   1.750   0.2822   0.03134   0.02050  -0.0376   0.7215   0.8587
   2.000   0.3022   0.03166   0.02086  -0.0368   0.7158   0.8687
   2.250   0.3310   0.03177   0.02100  -0.0372   0.7123   0.8794
   2.500   0.3434   0.03239   0.02168  -0.0359   0.7053   0.8928
   2.750   0.3644   0.03278   0.02213  -0.0355   0.6993   0.9063
   3.000   0.3979   0.03288   0.02230  -0.0367   0.6957   0.9190
   3.250   0.4163   0.03360   0.02312  -0.0367   0.6883   0.9365
   3.500   0.4497   0.03405   0.02366  -0.0388   0.6824   0.9526
   3.750   0.4964   0.03414   0.02386  -0.0424   0.6789   0.9673
   4.000   0.5131   0.03519   0.02500  -0.0433   0.6698   1.0000
   4.250   0.5382   0.03556   0.02542  -0.0438   0.6643   1.0000
   4.500   0.5758   0.03558   0.02551  -0.0456   0.6610   1.0000
   4.750   0.5751   0.03719   0.02716  -0.0440   0.6495   1.0000
   5.000   0.6126   0.03720   0.02726  -0.0454   0.6456   1.0000
   5.250   0.6185   0.03872   0.02883  -0.0445   0.6345   1.0000
   5.500   0.6554   0.03866   0.02890  -0.0456   0.6297   1.0000
   5.750   0.6649   0.04001   0.03032  -0.0447   0.6183   1.0000
   6.000   0.7047   0.03957   0.03004  -0.0456   0.6131   1.0000
   6.250   0.7154   0.04076   0.03132  -0.0446   0.6005   1.0000
   6.500   0.7631   0.03953   0.03030  -0.0455   0.5955   1.0000
   6.750   0.7749   0.04040   0.03129  -0.0441   0.5817   1.0000
   7.000   0.7935   0.04075   0.03178  -0.0430   0.5683   1.0000
   7.250   0.8205   0.04023   0.03145  -0.0420   0.5547   1.0000
   7.500   0.8513   0.03910   0.03050  -0.0407   0.5390   1.0000
   7.750   0.8794   0.03789   0.02947  -0.0391   0.5201   1.0000
   8.000   0.9140   0.03588   0.02763  -0.0373   0.4976   1.0000
   8.250   0.9130   0.03703   0.02891  -0.0348   0.4709   1.0000
   8.500   0.9188   0.03769   0.02968  -0.0326   0.4380   1.0000
   8.750   0.9251   0.03847   0.03052  -0.0307   0.3948   1.0000
   9.000   0.9529   0.03685   0.02831  -0.0277   0.3105   1.0000
   9.500   0.9458   0.04147   0.03194  -0.0238   0.2042   1.0000
   9.750   0.9410   0.04434   0.03451  -0.0225   0.1726   1.0000
  10.000   0.9395   0.04708   0.03705  -0.0216   0.1489   1.0000
  10.250   0.9404   0.04970   0.03951  -0.0207   0.1312   1.0000
  10.500   0.9442   0.05211   0.04184  -0.0200   0.1176   1.0000
  10.750   0.9506   0.05434   0.04400  -0.0192   0.1068   1.0000
  11.000   0.9586   0.05644   0.04597  -0.0185   0.0985   1.0000
  11.250   0.9718   0.05816   0.04783  -0.0178   0.0902   1.0000
  11.500   0.9862   0.05983   0.04946  -0.0170   0.0840   1.0000
  11.750   1.0044   0.06131   0.05110  -0.0162   0.0780   1.0000
  12.000   1.0253   0.06263   0.05238  -0.0154   0.0730   1.0000
  12.250   1.0482   0.06415   0.05418  -0.0147   0.0685   1.0000
  12.500   1.0676   0.06585   0.05594  -0.0142   0.0649   1.0000
  12.750   1.0862   0.06795   0.05819  -0.0138   0.0619   1.0000
  13.000   1.0969   0.07083   0.06140  -0.0135   0.0596   1.0000
  13.250   1.1047   0.07393   0.06477  -0.0134   0.0578   1.0000
  13.500   1.1094   0.07713   0.06816  -0.0135   0.0563   1.0000
  13.750   1.1154   0.08015   0.07129  -0.0136   0.0547   1.0000
  14.000   1.1160   0.08389   0.07517  -0.0140   0.0536   1.0000
  14.250   1.1017   0.08909   0.08073  -0.0152   0.0531   1.0000
  14.500   1.0845   0.09487   0.08684  -0.0170   0.0527   1.0000
  14.750   1.0649   0.10130   0.09357  -0.0196   0.0525   1.0000
  15.000   1.0421   0.10866   0.10120  -0.0232   0.0525   1.0000
  15.250   1.0169   0.11708   0.10985  -0.0278   0.0527   1.0000
  15.500   0.9900   0.12676   0.11971  -0.0337   0.0530   1.0000
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