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NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 50,000
Max Cl/Cd: 38.11 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a410-il-50000.txt
Download as CSV file: xf-naca64a410-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A410                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4052   0.09867   0.09190  -0.0237   1.0000   0.2911
  -8.000  -0.4047   0.09605   0.08936  -0.0225   1.0000   0.3064
  -7.750  -0.4090   0.09395   0.08735  -0.0208   1.0000   0.3231
  -7.500  -0.4209   0.09249   0.08603  -0.0184   1.0000   0.3395
  -7.250  -0.3998   0.08842   0.08195  -0.0162   1.0000   0.3634
  -7.000  -0.4182   0.08769   0.08138  -0.0125   1.0000   0.3831
  -6.750  -0.4111   0.08510   0.07884  -0.0091   1.0000   0.4118
  -6.500  -0.3867   0.08146   0.07515  -0.0063   1.0000   0.4518
  -6.250  -0.3861   0.07952   0.07328  -0.0024   1.0000   0.4831
  -6.000  -0.3793   0.07695   0.07076   0.0008   1.0000   0.5119
  -5.000  -0.4456   0.04886   0.04134  -0.0446   1.0000   0.1637
  -4.750  -0.4216   0.04434   0.03632  -0.0458   1.0000   0.1465
  -4.500  -0.3944   0.04080   0.03187  -0.0470   1.0000   0.1357
  -4.250  -0.3700   0.03766   0.02841  -0.0471   1.0000   0.1323
  -4.000  -0.3425   0.03486   0.02506  -0.0474   1.0000   0.1278
  -3.750  -0.3141   0.03258   0.02221  -0.0474   1.0000   0.1263
  -3.500  -0.2872   0.03084   0.02014  -0.0473   1.0000   0.1318
  -3.250  -0.2595   0.02932   0.01818  -0.0470   1.0000   0.1374
  -3.000  -0.2333   0.02771   0.01656  -0.0465   1.0000   0.1440
  -2.750  -0.2081   0.02648   0.01529  -0.0457   1.0000   0.1577
  -2.500  -0.1823   0.02541   0.01413  -0.0451   1.0000   0.1788
  -2.250  -0.1526   0.02385   0.01295  -0.0457   1.0000   0.2326
  -2.000  -0.1508   0.02080   0.01298  -0.0360   1.0000   0.8273
  -1.750  -0.1357   0.02039   0.01243  -0.0327   1.0000   1.0000
  -1.500  -0.1110   0.02062   0.01216  -0.0336   1.0000   1.0000
  -1.250  -0.0864   0.02092   0.01203  -0.0345   1.0000   1.0000
  -1.000  -0.0623   0.02128   0.01204  -0.0352   1.0000   1.0000
  -0.750  -0.0385   0.02169   0.01214  -0.0358   1.0000   1.0000
  -0.500  -0.0153   0.02214   0.01233  -0.0363   1.0000   1.0000
  -0.250   0.0076   0.02264   0.01257  -0.0368   1.0000   1.0000
   0.000   0.0301   0.02317   0.01290  -0.0372   1.0000   1.0000
   0.250   0.0522   0.02375   0.01330  -0.0376   1.0000   1.0000
   0.500   0.0740   0.02436   0.01376  -0.0379   1.0000   1.0000
   0.750   0.0955   0.02502   0.01426  -0.0383   1.0000   1.0000
   1.000   0.1167   0.02571   0.01484  -0.0386   1.0000   1.0000
   1.250   0.1376   0.02644   0.01548  -0.0389   1.0000   1.0000
   1.500   0.1581   0.02721   0.01617  -0.0391   1.0000   1.0000
   1.750   0.1784   0.02802   0.01692  -0.0394   1.0000   1.0000
   2.000   0.1984   0.02887   0.01772  -0.0397   1.0000   1.0000
   2.250   0.2182   0.02977   0.01858  -0.0399   1.0000   1.0000
   2.500   0.2453   0.03086   0.01966  -0.0417   0.9965   1.0000
   2.750   0.2855   0.03227   0.02109  -0.0459   0.9866   1.0000
   3.000   0.3222   0.03361   0.02248  -0.0494   0.9760   1.0000
   3.250   0.3585   0.03498   0.02391  -0.0528   0.9651   1.0000
   3.500   0.3968   0.03640   0.02544  -0.0564   0.9538   1.0000
   3.750   0.4348   0.03780   0.02695  -0.0599   0.9418   1.0000
   4.000   0.4671   0.03903   0.02831  -0.0622   0.9281   1.0000
   4.250   0.5034   0.04022   0.02969  -0.0649   0.9109   1.0000
   4.500   0.5363   0.04119   0.03084  -0.0667   0.8907   1.0000
   4.750   0.5852   0.04199   0.03189  -0.0703   0.8669   1.0000
   5.000   0.6340   0.04233   0.03256  -0.0732   0.8413   1.0000
   5.250   0.6706   0.04249   0.03301  -0.0739   0.8159   1.0000
   5.500   0.7143   0.04218   0.03306  -0.0749   0.7898   1.0000
   5.750   0.7724   0.04044   0.03187  -0.0759   0.7592   1.0000
   6.000   0.8831   0.03010   0.02255  -0.0718   0.6915   1.0000
   6.250   0.9104   0.02389   0.01618  -0.0584   0.4895   1.0000
   6.500   0.8892   0.02756   0.01718  -0.0496   0.2375   1.0000
   6.750   0.8949   0.03064   0.01952  -0.0462   0.1762   1.0000
   7.000   0.9277   0.03326   0.02170  -0.0460   0.1417   1.0000
   7.250   0.9812   0.03641   0.02481  -0.0483   0.1229   1.0000
   7.500   1.0189   0.03968   0.02810  -0.0493   0.1115   1.0000
   7.750   1.0463   0.04252   0.03147  -0.0484   0.1073   1.0000
   8.000   1.0712   0.04587   0.03529  -0.0474   0.1054   1.0000
   8.250   1.0907   0.04941   0.03932  -0.0459   0.1045   1.0000
   8.500   1.1057   0.05294   0.04326  -0.0441   0.1029   1.0000
   8.750   1.1190   0.05669   0.04732  -0.0425   0.1011   1.0000
   9.000   1.1224   0.06061   0.05187  -0.0397   0.1022   1.0000
   9.250   1.1184   0.06508   0.05695  -0.0367   0.1054   1.0000
   9.500   1.1150   0.06980   0.06207  -0.0343   0.1086   1.0000
   9.750   1.1281   0.07590   0.06823  -0.0338   0.1122   1.0000
  10.000   1.0873   0.07903   0.07207  -0.0293   0.1170   1.0000
  10.250   1.0578   0.08368   0.07696  -0.0270   0.1205   1.0000
  10.500   1.0586   0.08965   0.08306  -0.0267   0.1280   1.0000
  10.750   1.0101   0.09471   0.08824  -0.0270   0.1294   1.0000
  11.000   0.9562   0.10350   0.09709  -0.0326   0.1327   1.0000
  11.250   0.9096   0.12149   0.11502  -0.0470   0.1702   1.0000
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