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NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-64 (naca001064-il)
Reynolds number: 50,000
Max Cl/Cd: 25.17 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001064-il-50000-n5.txt
Download as CSV file: xf-naca001064-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-64                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6931   0.09210   0.08460  -0.0246   1.0000   0.0631
 -10.500  -0.7120   0.08500   0.07750  -0.0291   1.0000   0.0625
 -10.250  -0.7341   0.07902   0.07146  -0.0316   1.0000   0.0620
 -10.000  -0.7570   0.07415   0.06650  -0.0318   1.0000   0.0616
  -9.750  -0.7776   0.06990   0.06214  -0.0304   1.0000   0.0615
  -9.500  -0.7925   0.06566   0.05768  -0.0287   1.0000   0.0615
  -9.250  -0.8032   0.06158   0.05331  -0.0267   1.0000   0.0619
  -9.000  -0.8106   0.05771   0.04906  -0.0243   1.0000   0.0630
  -8.750  -0.8154   0.05401   0.04482  -0.0215   1.0000   0.0646
  -8.500  -0.8156   0.05059   0.04088  -0.0187   1.0000   0.0661
  -8.250  -0.8048   0.04783   0.03799  -0.0172   1.0000   0.0679
  -8.000  -0.7934   0.04518   0.03506  -0.0153   1.0000   0.0693
  -7.750  -0.7804   0.04282   0.03241  -0.0135   1.0000   0.0715
  -7.500  -0.7668   0.04067   0.02989  -0.0116   1.0000   0.0751
  -7.250  -0.7515   0.03841   0.02711  -0.0096   1.0000   0.0781
  -7.000  -0.7322   0.03616   0.02453  -0.0082   1.0000   0.0800
  -6.750  -0.7109   0.03428   0.02252  -0.0072   1.0000   0.0824
  -6.500  -0.6891   0.03270   0.02078  -0.0062   1.0000   0.0858
  -6.250  -0.6670   0.03135   0.01915  -0.0051   1.0000   0.0915
  -6.000  -0.6434   0.02994   0.01770  -0.0043   1.0000   0.0964
  -5.750  -0.6191   0.02868   0.01635  -0.0035   1.0000   0.1013
  -5.500  -0.5943   0.02756   0.01503  -0.0025   1.0000   0.1075
  -5.250  -0.5729   0.02645   0.01397  -0.0014   1.0000   0.1150
  -5.000  -0.5527   0.02547   0.01299  -0.0001   1.0000   0.1276
  -4.750  -0.5340   0.02449   0.01207   0.0014   1.0000   0.1465
  -4.500  -0.5166   0.02341   0.01113   0.0031   1.0000   0.1733
  -4.000  -0.4908   0.02061   0.00952   0.0074   1.0000   0.3395
  -3.750  -0.4827   0.01919   0.00951   0.0120   1.0000   0.5714
  -3.500  -0.4534   0.01935   0.01013   0.0146   1.0000   0.7361
  -3.250  -0.4216   0.01983   0.01053   0.0159   1.0000   0.8088
  -3.000  -0.3796   0.02058   0.01107   0.0155   1.0000   0.8653
  -2.750  -0.3209   0.02132   0.01146   0.0114   1.0000   0.9063
  -2.500  -0.2444   0.02173   0.01150   0.0029   1.0000   0.9381
  -2.250  -0.1882   0.02165   0.01117  -0.0028   1.0000   0.9598
  -2.000  -0.1443   0.02137   0.01071  -0.0067   1.0000   0.9733
  -1.750  -0.1013   0.02105   0.01025  -0.0105   1.0000   0.9849
  -1.500  -0.0585   0.02069   0.00979  -0.0145   1.0000   0.9952
  -1.250  -0.0334   0.02042   0.00947  -0.0151   1.0000   1.0000
  -1.000  -0.0253   0.02026   0.00929  -0.0124   1.0000   1.0000
  -0.750  -0.0180   0.02013   0.00916  -0.0095   1.0000   1.0000
  -0.500  -0.0116   0.02005   0.00907  -0.0064   1.0000   1.0000
  -0.250  -0.0056   0.02000   0.00902  -0.0032   1.0000   1.0000
   0.000   0.0000   0.01998   0.00900   0.0000   1.0000   1.0000
   0.250   0.0056   0.02000   0.00902   0.0032   1.0000   1.0000
   0.500   0.0115   0.02005   0.00907   0.0064   1.0000   1.0000
   0.750   0.0180   0.02013   0.00916   0.0095   1.0000   1.0000
   1.000   0.0253   0.02025   0.00929   0.0124   1.0000   1.0000
   1.250   0.0334   0.02041   0.00946   0.0151   1.0000   1.0000
   1.500   0.0585   0.02068   0.00978   0.0145   0.9952   1.0000
   1.750   0.1013   0.02104   0.01025   0.0105   0.9849   1.0000
   2.000   0.1443   0.02137   0.01071   0.0067   0.9733   1.0000
   2.250   0.1881   0.02165   0.01117   0.0028   0.9599   1.0000
   2.500   0.2443   0.02173   0.01149  -0.0029   0.9382   1.0000
   2.750   0.3209   0.02132   0.01146  -0.0114   0.9063   1.0000
   3.000   0.3796   0.02058   0.01106  -0.0155   0.8654   1.0000
   3.250   0.4215   0.01983   0.01052  -0.0159   0.8089   1.0000
   3.500   0.4534   0.01934   0.01013  -0.0146   0.7362   1.0000
   3.750   0.4827   0.01918   0.00951  -0.0120   0.5717   1.0000
   4.000   0.4908   0.02060   0.00951  -0.0074   0.3397   1.0000
   4.500   0.5166   0.02341   0.01113  -0.0031   0.1734   1.0000
   4.750   0.5340   0.02449   0.01207  -0.0014   0.1464   1.0000
   5.000   0.5527   0.02547   0.01299   0.0001   0.1276   1.0000
   5.250   0.5729   0.02645   0.01397   0.0014   0.1150   1.0000
   5.500   0.5943   0.02756   0.01502   0.0025   0.1075   1.0000
   5.750   0.6191   0.02868   0.01635   0.0035   0.1013   1.0000
   6.000   0.6434   0.02994   0.01770   0.0043   0.0964   1.0000
   6.250   0.6670   0.03135   0.01915   0.0051   0.0915   1.0000
   6.500   0.6891   0.03270   0.02078   0.0062   0.0858   1.0000
   6.750   0.7109   0.03428   0.02252   0.0072   0.0824   1.0000
   7.000   0.7322   0.03616   0.02453   0.0082   0.0800   1.0000
   7.250   0.7515   0.03841   0.02711   0.0096   0.0781   1.0000
   7.500   0.7668   0.04066   0.02989   0.0116   0.0751   1.0000
   7.750   0.7804   0.04281   0.03241   0.0135   0.0715   1.0000
   8.000   0.7935   0.04518   0.03506   0.0153   0.0693   1.0000
   8.250   0.8048   0.04783   0.03799   0.0172   0.0679   1.0000
   8.500   0.8157   0.05059   0.04088   0.0187   0.0661   1.0000
   8.750   0.8154   0.05402   0.04483   0.0215   0.0646   1.0000
   9.000   0.8107   0.05772   0.04907   0.0243   0.0630   1.0000
   9.250   0.8034   0.06159   0.05332   0.0266   0.0619   1.0000
   9.500   0.7927   0.06567   0.05769   0.0287   0.0615   1.0000
   9.750   0.7779   0.06992   0.06216   0.0303   0.0615   1.0000
  10.000   0.7572   0.07419   0.06653   0.0317   0.0616   1.0000
  10.250   0.7345   0.07907   0.07151   0.0315   0.0620   1.0000
  10.500   0.7124   0.08506   0.07755   0.0289   0.0625   1.0000
  10.750   0.6936   0.09218   0.08468   0.0244   0.0631   1.0000
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