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NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A-010 10.0% (naca64a010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 58.14 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a010-il-1000000.txt
Download as CSV file: xf-naca64a010-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7715   0.06552   0.06374  -0.0317   1.0000   0.0087
 -11.250  -0.7985   0.05836   0.05646  -0.0362   1.0000   0.0086
 -11.000  -0.8317   0.05190   0.04982  -0.0378   1.0000   0.0085
 -10.750  -0.8652   0.04647   0.04417  -0.0360   1.0000   0.0084
 -10.500  -0.9074   0.04092   0.03830  -0.0300   1.0000   0.0082
 -10.250  -0.9366   0.03485   0.03178  -0.0246   1.0000   0.0082
 -10.000  -0.9470   0.03047   0.02698  -0.0205   1.0000   0.0083
  -9.750  -0.9461   0.02726   0.02341  -0.0172   1.0000   0.0085
  -9.500  -0.9345   0.02560   0.02153  -0.0151   1.0000   0.0088
  -9.250  -0.9196   0.02440   0.02016  -0.0133   1.0000   0.0091
  -9.000  -0.8998   0.02418   0.01984  -0.0121   1.0000   0.0093
  -8.750  -0.8953   0.02042   0.01565  -0.0088   1.0000   0.0096
  -8.500  -0.8820   0.01848   0.01353  -0.0066   1.0000   0.0100
  -8.250  -0.8639   0.01762   0.01260  -0.0051   1.0000   0.0103
  -8.000  -0.8447   0.01700   0.01192  -0.0037   1.0000   0.0107
  -7.750  -0.8260   0.01627   0.01112  -0.0022   1.0000   0.0110
  -7.500  -0.8070   0.01565   0.01043  -0.0007   1.0000   0.0114
  -7.250  -0.7891   0.01489   0.00959   0.0011   1.0000   0.0117
  -7.000  -0.7707   0.01430   0.00895   0.0028   1.0000   0.0122
  -6.750  -0.7523   0.01381   0.00841   0.0045   1.0000   0.0127
  -6.500  -0.7322   0.01354   0.00810   0.0059   0.9999   0.0131
  -6.250  -0.7017   0.01229   0.00673   0.0048   0.9977   0.0140
  -6.000  -0.6693   0.01149   0.00587   0.0033   0.9951   0.0149
  -5.750  -0.6367   0.01106   0.00543   0.0020   0.9920   0.0159
  -5.500  -0.6036   0.01062   0.00496   0.0006   0.9888   0.0169
  -5.250  -0.5688   0.01025   0.00455  -0.0011   0.9863   0.0181
  -5.000  -0.5379   0.00981   0.00406  -0.0020   0.9812   0.0194
  -4.750  -0.5046   0.00929   0.00352  -0.0034   0.9773   0.0223
  -4.500  -0.4719   0.00900   0.00321  -0.0046   0.9715   0.0248
  -4.250  -0.4378   0.00862   0.00283  -0.0061   0.9654   0.0305
  -4.000  -0.4059   0.00831   0.00253  -0.0072   0.9557   0.0402
  -3.750  -0.3752   0.00793   0.00227  -0.0080   0.9439   0.0681
  -3.500  -0.3484   0.00742   0.00199  -0.0080   0.9286   0.1316
  -3.250  -0.3261   0.00675   0.00169  -0.0072   0.9114   0.2419
  -3.000  -0.3074   0.00591   0.00139  -0.0058   0.8942   0.3953
  -2.750  -0.2861   0.00544   0.00124  -0.0046   0.8784   0.5017
  -2.500  -0.2618   0.00526   0.00116  -0.0039   0.8641   0.5500
  -2.250  -0.2363   0.00516   0.00109  -0.0034   0.8508   0.5795
  -2.000  -0.2104   0.00509   0.00104  -0.0029   0.8383   0.6042
  -1.750  -0.1848   0.00501   0.00100  -0.0024   0.8262   0.6325
  -1.500  -0.1590   0.00495   0.00098  -0.0019   0.8148   0.6587
  -1.250  -0.1335   0.00490   0.00096  -0.0014   0.8039   0.6850
  -1.000  -0.1071   0.00488   0.00094  -0.0011   0.7933   0.7033
  -0.750  -0.0805   0.00486   0.00093  -0.0008   0.7829   0.7184
  -0.500  -0.0538   0.00485   0.00093  -0.0005   0.7728   0.7322
  -0.250  -0.0271   0.00484   0.00092  -0.0002   0.7628   0.7432
   0.000   0.0000   0.00483   0.00092   0.0000   0.7529   0.7529
   0.250   0.0272   0.00484   0.00092   0.0002   0.7432   0.7628
   0.500   0.0539   0.00485   0.00093   0.0004   0.7322   0.7728
   0.750   0.0805   0.00486   0.00093   0.0007   0.7185   0.7829
   1.000   0.1071   0.00488   0.00094   0.0010   0.7035   0.7933
   1.250   0.1335   0.00490   0.00096   0.0014   0.6846   0.8039
   1.500   0.1591   0.00495   0.00098   0.0019   0.6588   0.8148
   1.750   0.1848   0.00501   0.00100   0.0024   0.6327   0.8263
   2.000   0.2104   0.00509   0.00104   0.0029   0.6040   0.8383
   2.250   0.2363   0.00516   0.00110   0.0034   0.5799   0.8508
   2.500   0.2618   0.00525   0.00116   0.0039   0.5508   0.8640
   2.750   0.2860   0.00545   0.00124   0.0046   0.5010   0.8784
   3.000   0.3073   0.00593   0.00139   0.0058   0.3917   0.8942
   3.250   0.3261   0.00675   0.00169   0.0072   0.2413   0.9114
   3.500   0.3484   0.00741   0.00199   0.0080   0.1329   0.9285
   3.750   0.3751   0.00793   0.00227   0.0080   0.0683   0.9439
   4.000   0.4058   0.00831   0.00253   0.0072   0.0405   0.9557
   4.250   0.4378   0.00862   0.00283   0.0061   0.0303   0.9654
   4.500   0.4719   0.00900   0.00321   0.0046   0.0249   0.9714
   4.750   0.5046   0.00929   0.00352   0.0034   0.0222   0.9774
   5.000   0.5376   0.00986   0.00412   0.0020   0.0191   0.9813
   5.250   0.5689   0.01022   0.00452   0.0011   0.0180   0.9863
   5.500   0.6036   0.01061   0.00494  -0.0006   0.0169   0.9888
   5.750   0.6368   0.01104   0.00540  -0.0020   0.0158   0.9920
   6.000   0.6692   0.01151   0.00590  -0.0033   0.0149   0.9951
   6.250   0.7015   0.01232   0.00676  -0.0047   0.0140   0.9977
   6.500   0.7323   0.01350   0.00806  -0.0059   0.0131   0.9999
   6.750   0.7527   0.01378   0.00837  -0.0046   0.0126   1.0000
   7.000   0.7704   0.01436   0.00901  -0.0027   0.0122   1.0000
   7.250   0.7889   0.01493   0.00964  -0.0010   0.0117   1.0000
   7.500   0.8070   0.01566   0.01045   0.0007   0.0113   1.0000
   7.750   0.8257   0.01635   0.01121   0.0023   0.0110   1.0000
   8.000   0.8443   0.01712   0.01206   0.0038   0.0107   1.0000
   8.250   0.8632   0.01781   0.01281   0.0052   0.0104   1.0000
   8.500   0.8818   0.01854   0.01359   0.0066   0.0100   1.0000
   8.750   0.8964   0.02018   0.01538   0.0086   0.0097   1.0000
   9.000   0.8999   0.02415   0.01981   0.0120   0.0093   1.0000
   9.250   0.9186   0.02458   0.02037   0.0134   0.0091   1.0000
   9.500   0.9344   0.02560   0.02154   0.0151   0.0088   1.0000
   9.750   0.9449   0.02746   0.02363   0.0173   0.0086   1.0000
  10.000   0.9479   0.03032   0.02681   0.0204   0.0083   1.0000
  10.250   0.9377   0.03470   0.03161   0.0245   0.0082   1.0000
  10.500   0.9096   0.04068   0.03805   0.0298   0.0082   1.0000
  10.750   0.8614   0.04699   0.04471   0.0362   0.0084   1.0000
  11.000   0.8303   0.05214   0.05007   0.0377   0.0085   1.0000
  11.250   0.8031   0.05765   0.05572   0.0363   0.0086   1.0000
  11.500   0.7691   0.06616   0.06439   0.0312   0.0087   1.0000
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