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NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 642-015A AIRFOIL (n64015a-il)
Reynolds number: 50,000
Max Cl/Cd: 28.61 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64015a-il-50000.txt
Download as CSV file: xf-n64015a-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015A AIRFOIL                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6976   0.09939   0.09208  -0.0278   1.0000   0.1445
 -11.500  -0.7049   0.09283   0.08553  -0.0301   1.0000   0.1418
 -11.250  -0.8211   0.07971   0.07217  -0.0378   1.0000   0.1301
 -11.000  -0.8309   0.07491   0.06728  -0.0375   1.0000   0.1286
 -10.750  -0.8503   0.07069   0.06293  -0.0358   1.0000   0.1272
 -10.500  -0.8694   0.06673   0.05877  -0.0336   1.0000   0.1260
 -10.250  -0.8845   0.06288   0.05464  -0.0311   1.0000   0.1251
 -10.000  -0.8938   0.05928   0.05074  -0.0285   1.0000   0.1249
  -9.750  -0.8978   0.05593   0.04705  -0.0259   1.0000   0.1255
  -9.500  -0.8979   0.05277   0.04352  -0.0233   1.0000   0.1266
  -9.250  -0.8944   0.04975   0.04011  -0.0208   1.0000   0.1278
  -9.000  -0.8868   0.04686   0.03679  -0.0183   1.0000   0.1292
  -8.750  -0.8775   0.04434   0.03376  -0.0157   1.0000   0.1310
  -8.500  -0.8514   0.04140   0.03099  -0.0158   1.0000   0.1375
  -8.250  -0.8345   0.03925   0.02849  -0.0141   1.0000   0.1437
  -8.000  -0.8059   0.03677   0.02604  -0.0140   1.0000   0.1524
  -7.750  -0.7771   0.03466   0.02392  -0.0139   1.0000   0.1656
  -7.500  -0.7456   0.03267   0.02205  -0.0139   1.0000   0.1851
  -7.250  -0.7187   0.03074   0.02040  -0.0133   1.0000   0.2135
  -7.000  -0.7076   0.02884   0.01889  -0.0105   1.0000   0.2528
  -6.750  -0.7134   0.02674   0.01763  -0.0053   1.0000   0.3088
  -6.500  -0.7304   0.02553   0.01807   0.0035   1.0000   0.4498
  -6.250  -0.7315   0.02801   0.02087   0.0135   1.0000   0.5744
  -6.000  -0.6806   0.03350   0.02609   0.0192   1.0000   0.6389
  -5.750  -0.4984   0.04376   0.03528   0.0129   1.0000   0.7069
  -5.500  -0.4401   0.04492   0.03607   0.0116   1.0000   0.7415
  -5.250  -0.3733   0.04506   0.03587   0.0076   1.0000   0.7694
  -5.000  -0.3558   0.04438   0.03506   0.0087   1.0000   0.7907
  -4.750  -0.3166   0.04358   0.03409   0.0067   1.0000   0.8104
  -4.500  -0.2877   0.04271   0.03311   0.0057   1.0000   0.8275
  -4.250  -0.2715   0.04193   0.03226   0.0063   1.0000   0.8423
  -4.000  -0.2497   0.04115   0.03141   0.0061   1.0000   0.8560
  -3.750  -0.2243   0.04033   0.03053   0.0051   1.0000   0.8684
  -3.500  -0.2160   0.03977   0.02994   0.0067   1.0000   0.8791
  -3.250  -0.2194   0.03946   0.02961   0.0100   1.0000   0.8891
  -3.000  -0.2021   0.03889   0.02900   0.0098   1.0000   0.8987
  -2.750  -0.2126   0.03870   0.02881   0.0141   1.0000   0.9078
  -2.500  -0.1898   0.03817   0.02822   0.0127   1.0000   0.9166
  -2.250  -0.1901   0.03789   0.02793   0.0151   1.0000   0.9253
  -2.000  -0.1704   0.03750   0.02748   0.0141   1.0000   0.9338
  -1.750  -0.1622   0.03721   0.02717   0.0149   1.0000   0.9422
  -1.500  -0.1428   0.03691   0.02683   0.0137   1.0000   0.9507
  -1.250  -0.1259   0.03666   0.02655   0.0129   1.0000   0.9590
  -1.000  -0.1062   0.03647   0.02633   0.0115   1.0000   0.9678
  -0.750  -0.0800   0.03628   0.02612   0.0088   1.0000   0.9761
  -0.500  -0.0536   0.03617   0.02600   0.0061   1.0000   0.9851
  -0.250  -0.0218   0.03612   0.02593   0.0022   1.0000   0.9943
   0.000   0.0000   0.03611   0.02592   0.0000   1.0000   1.0000
   0.250   0.0218   0.03612   0.02593  -0.0022   0.9943   1.0000
   0.500   0.0535   0.03617   0.02600  -0.0061   0.9851   1.0000
   0.750   0.0800   0.03627   0.02612  -0.0088   0.9761   1.0000
   1.000   0.1061   0.03646   0.02632  -0.0115   0.9678   1.0000
   1.250   0.1259   0.03665   0.02654  -0.0129   0.9590   1.0000
   1.500   0.1428   0.03690   0.02682  -0.0137   0.9507   1.0000
   1.750   0.1621   0.03719   0.02715  -0.0149   0.9422   1.0000
   2.000   0.1703   0.03748   0.02747  -0.0141   0.9338   1.0000
   2.250   0.1899   0.03787   0.02791  -0.0151   0.9253   1.0000
   2.500   0.1897   0.03815   0.02821  -0.0127   0.9166   1.0000
   2.750   0.2124   0.03868   0.02878  -0.0140   0.9078   1.0000
   3.000   0.2019   0.03887   0.02898  -0.0098   0.8987   1.0000
   3.250   0.2194   0.03944   0.02959  -0.0100   0.8891   1.0000
   3.500   0.2159   0.03975   0.02992  -0.0066   0.8791   1.0000
   3.750   0.2243   0.04031   0.03050  -0.0051   0.8684   1.0000
   4.000   0.2498   0.04113   0.03139  -0.0061   0.8560   1.0000
   4.250   0.2714   0.04191   0.03224  -0.0063   0.8424   1.0000
   4.500   0.2878   0.04269   0.03308  -0.0057   0.8275   1.0000
   4.750   0.3168   0.04356   0.03407  -0.0067   0.8104   1.0000
   5.000   0.3562   0.04436   0.03505  -0.0088   0.7907   1.0000
   5.250   0.3737   0.04505   0.03585  -0.0077   0.7694   1.0000
   5.500   0.4404   0.04490   0.03605  -0.0116   0.7415   1.0000
   5.750   0.4987   0.04374   0.03526  -0.0130   0.7069   1.0000
   6.000   0.6806   0.03350   0.02608  -0.0192   0.6390   1.0000
   6.250   0.7315   0.02801   0.02087  -0.0135   0.5746   1.0000
   6.500   0.7304   0.02553   0.01806  -0.0035   0.4502   1.0000
   6.750   0.7134   0.02673   0.01763   0.0053   0.3090   1.0000
   7.000   0.7076   0.02883   0.01889   0.0105   0.2528   1.0000
   7.250   0.7187   0.03073   0.02039   0.0133   0.2136   1.0000
   7.500   0.7455   0.03267   0.02204   0.0139   0.1851   1.0000
   7.750   0.7771   0.03465   0.02392   0.0139   0.1657   1.0000
   8.000   0.8059   0.03677   0.02603   0.0140   0.1524   1.0000
   8.250   0.8345   0.03925   0.02849   0.0141   0.1437   1.0000
   8.500   0.8514   0.04140   0.03099   0.0158   0.1375   1.0000
   8.750   0.8775   0.04434   0.03376   0.0157   0.1310   1.0000
   9.000   0.8869   0.04686   0.03678   0.0183   0.1292   1.0000
   9.250   0.8945   0.04975   0.04011   0.0207   0.1278   1.0000
   9.500   0.8980   0.05277   0.04352   0.0233   0.1266   1.0000
   9.750   0.8980   0.05593   0.04705   0.0259   0.1255   1.0000
  10.000   0.8940   0.05929   0.05075   0.0285   0.1249   1.0000
  10.250   0.8847   0.06289   0.05466   0.0310   0.1251   1.0000
  10.500   0.8697   0.06674   0.05879   0.0335   0.1260   1.0000
  10.750   0.8508   0.07072   0.06296   0.0357   0.1273   1.0000
  11.000   0.8314   0.07495   0.06733   0.0373   0.1286   1.0000
  11.250   0.8220   0.07976   0.07222   0.0377   0.1302   1.0000
  11.500   0.7056   0.09292   0.08562   0.0299   0.1418   1.0000
  11.750   0.6985   0.09946   0.09215   0.0277   0.1445   1.0000
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