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NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A-010 10.0% (naca64a010-il)
Reynolds number: 500,000
Max Cl/Cd: 49.94 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a010-il-500000-n5.txt
Download as CSV file: xf-naca64a010-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A-010 10.0%                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7039   0.09627   0.09393  -0.0113   1.0000   0.0078
 -11.750  -0.8996   0.04915   0.04622  -0.0377   1.0000   0.0070
 -11.500  -0.9176   0.04526   0.04214  -0.0370   1.0000   0.0071
 -11.250  -0.9369   0.04162   0.03826  -0.0347   1.0000   0.0072
 -11.000  -0.9504   0.03885   0.03527  -0.0313   1.0000   0.0073
 -10.750  -0.9582   0.03651   0.03271  -0.0276   1.0000   0.0074
 -10.500  -0.9623   0.03359   0.02948  -0.0245   1.0000   0.0075
 -10.250  -0.9601   0.03106   0.02666  -0.0218   1.0000   0.0077
 -10.000  -0.9540   0.02873   0.02403  -0.0194   1.0000   0.0079
  -9.750  -0.9440   0.02676   0.02179  -0.0172   1.0000   0.0082
  -9.500  -0.9309   0.02515   0.01994  -0.0154   1.0000   0.0085
  -9.250  -0.9163   0.02363   0.01820  -0.0136   1.0000   0.0087
  -9.000  -0.9002   0.02233   0.01668  -0.0120   1.0000   0.0090
  -8.750  -0.8833   0.02117   0.01535  -0.0104   1.0000   0.0091
  -8.500  -0.8653   0.02022   0.01425  -0.0089   1.0000   0.0093
  -8.250  -0.8505   0.01878   0.01266  -0.0070   1.0000   0.0098
  -8.000  -0.8317   0.01813   0.01197  -0.0057   1.0000   0.0102
  -7.750  -0.8121   0.01758   0.01137  -0.0044   1.0000   0.0107
  -7.500  -0.7923   0.01707   0.01081  -0.0031   1.0000   0.0113
  -7.250  -0.7736   0.01640   0.01004  -0.0016   1.0000   0.0117
  -7.000  -0.7552   0.01574   0.00931   0.0001   1.0000   0.0122
  -6.750  -0.7367   0.01516   0.00865   0.0017   1.0000   0.0127
  -6.500  -0.7156   0.01458   0.00800   0.0028   0.9994   0.0130
  -6.250  -0.6849   0.01380   0.00715   0.0017   0.9950   0.0137
  -6.000  -0.6553   0.01311   0.00641   0.0008   0.9898   0.0146
  -5.750  -0.6233   0.01272   0.00601  -0.0004   0.9851   0.0161
  -5.500  -0.5930   0.01228   0.00552  -0.0012   0.9788   0.0173
  -5.250  -0.5611   0.01187   0.00506  -0.0024   0.9729   0.0184
  -5.000  -0.5293   0.01135   0.00448  -0.0035   0.9662   0.0204
  -4.750  -0.4975   0.01097   0.00409  -0.0046   0.9579   0.0229
  -4.500  -0.4637   0.01067   0.00375  -0.0061   0.9497   0.0258
  -4.000  -0.4002   0.00999   0.00309  -0.0082   0.9262   0.0414
  -3.750  -0.3707   0.00970   0.00282  -0.0087   0.9120   0.0574
  -3.500  -0.3443   0.00932   0.00255  -0.0086   0.8967   0.0925
  -3.250  -0.3206   0.00881   0.00226  -0.0080   0.8812   0.1621
  -3.000  -0.2997   0.00811   0.00195  -0.0070   0.8661   0.2755
  -2.750  -0.2800   0.00738   0.00168  -0.0057   0.8519   0.4057
  -2.500  -0.2580   0.00697   0.00156  -0.0047   0.8386   0.4964
  -2.250  -0.2343   0.00675   0.00147  -0.0038   0.8265   0.5509
  -2.000  -0.2101   0.00658   0.00142  -0.0031   0.8152   0.5965
  -1.750  -0.1860   0.00645   0.00139  -0.0022   0.8043   0.6419
  -1.500  -0.1607   0.00638   0.00137  -0.0016   0.7933   0.6691
  -1.250  -0.1344   0.00634   0.00133  -0.0012   0.7831   0.6861
  -1.000  -0.1078   0.00632   0.00130  -0.0009   0.7736   0.6987
  -0.750  -0.0810   0.00631   0.00127  -0.0006   0.7636   0.7080
  -0.500  -0.0539   0.00631   0.00125  -0.0004   0.7538   0.7172
  -0.250  -0.0270   0.00630   0.00123  -0.0002   0.7448   0.7261
   0.000   0.0000   0.00630   0.00123   0.0000   0.7354   0.7354
   0.250   0.0270   0.00630   0.00123   0.0002   0.7261   0.7448
   0.500   0.0539   0.00631   0.00125   0.0004   0.7172   0.7538
   0.750   0.0810   0.00631   0.00127   0.0006   0.7080   0.7636
   1.000   0.1079   0.00632   0.00130   0.0009   0.6987   0.7737
   1.250   0.1344   0.00634   0.00133   0.0012   0.6862   0.7831
   1.500   0.1608   0.00638   0.00137   0.0016   0.6691   0.7933
   1.750   0.1861   0.00645   0.00139   0.0022   0.6418   0.8042
   2.000   0.2101   0.00658   0.00142   0.0031   0.5965   0.8152
   2.250   0.2342   0.00675   0.00147   0.0038   0.5504   0.8264
   2.500   0.2580   0.00698   0.00155   0.0047   0.4954   0.8386
   2.750   0.2800   0.00739   0.00168   0.0057   0.4043   0.8519
   3.000   0.2998   0.00809   0.00195   0.0070   0.2781   0.8660
   3.250   0.3206   0.00880   0.00226   0.0080   0.1630   0.8812
   3.500   0.3443   0.00931   0.00255   0.0086   0.0936   0.8967
   3.750   0.3708   0.00970   0.00282   0.0086   0.0581   0.9121
   4.000   0.4002   0.00999   0.00309   0.0081   0.0415   0.9264
   4.250   0.4315   0.01030   0.00339   0.0072   0.0325   0.9388
   4.500   0.4637   0.01067   0.00375   0.0061   0.0259   0.9497
   4.750   0.4975   0.01097   0.00409   0.0046   0.0229   0.9578
   5.000   0.5293   0.01135   0.00448   0.0035   0.0203   0.9661
   5.250   0.5612   0.01186   0.00504   0.0024   0.0183   0.9728
   5.500   0.5930   0.01228   0.00552   0.0012   0.0173   0.9788
   5.750   0.6234   0.01270   0.00598   0.0004   0.0159   0.9851
   6.000   0.6552   0.01312   0.00643  -0.0008   0.0147   0.9898
   6.250   0.6848   0.01381   0.00716  -0.0016   0.0136   0.9951
   6.500   0.7155   0.01458   0.00800  -0.0027   0.0130   0.9994
   6.750   0.7370   0.01513   0.00863  -0.0017   0.0126   1.0000
   7.000   0.7552   0.01575   0.00932  -0.0001   0.0121   1.0000
   7.250   0.7737   0.01640   0.01004   0.0016   0.0117   1.0000
   7.500   0.7924   0.01707   0.01081   0.0031   0.0112   1.0000
   7.750   0.8118   0.01765   0.01145   0.0044   0.0107   1.0000
   8.000   0.8313   0.01821   0.01206   0.0057   0.0103   1.0000
   8.250   0.8502   0.01883   0.01273   0.0070   0.0098   1.0000
   8.500   0.8649   0.02029   0.01431   0.0090   0.0093   1.0000
   8.750   0.8831   0.02120   0.01537   0.0104   0.0092   1.0000
   9.000   0.9002   0.02232   0.01667   0.0120   0.0090   1.0000
   9.250   0.9165   0.02358   0.01814   0.0136   0.0087   1.0000
   9.500   0.9308   0.02515   0.01994   0.0154   0.0084   1.0000
   9.750   0.9433   0.02689   0.02193   0.0173   0.0083   1.0000
  10.000   0.9531   0.02888   0.02420   0.0195   0.0080   1.0000
  10.250   0.9603   0.03102   0.02661   0.0218   0.0077   1.0000
  10.500   0.9621   0.03362   0.02952   0.0245   0.0076   1.0000
  10.750   0.9616   0.03605   0.03221   0.0273   0.0073   1.0000
  11.000   0.9494   0.03897   0.03540   0.0314   0.0073   1.0000
  11.250   0.9297   0.04244   0.03914   0.0351   0.0072   1.0000
  11.500   0.9203   0.04497   0.04183   0.0369   0.0071   1.0000
  11.750   0.8692   0.05324   0.05047   0.0369   0.0071   1.0000
  12.000   0.7061   0.09595   0.09361   0.0114   0.0078   1.0000
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