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NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 50,000
Max Cl/Cd: 37.52 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a410-il-50000-n5.txt
Download as CSV file: xf-naca64a410-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3381   0.09549   0.08886  -0.0425   1.0000   0.0688
  -9.250  -0.3417   0.09171   0.08513  -0.0427   1.0000   0.0665
  -9.000  -0.4415   0.09582   0.08886  -0.0447   1.0000   0.0604
  -8.750  -0.4357   0.09256   0.08563  -0.0435   1.0000   0.0580
  -8.500  -0.4406   0.08905   0.08222  -0.0440   1.0000   0.0564
  -8.250  -0.4510   0.08563   0.07892  -0.0444   1.0000   0.0551
  -7.750  -0.4915   0.07518   0.06846  -0.0513   1.0000   0.0490
  -7.500  -0.4939   0.07188   0.06516  -0.0504   1.0000   0.0486
  -7.250  -0.4977   0.06839   0.06160  -0.0498   1.0000   0.0484
  -7.000  -0.5003   0.06474   0.05780  -0.0495   1.0000   0.0484
  -6.750  -0.5004   0.06095   0.05378  -0.0493   1.0000   0.0486
  -6.500  -0.4972   0.05712   0.04960  -0.0492   1.0000   0.0489
  -6.000  -0.4793   0.04979   0.04164  -0.0486   1.0000   0.0495
  -5.750  -0.4651   0.04647   0.03788  -0.0482   1.0000   0.0493
  -5.500  -0.4488   0.04319   0.03418  -0.0479   1.0000   0.0494
  -5.250  -0.4306   0.04007   0.03067  -0.0476   1.0000   0.0498
  -5.000  -0.4114   0.03757   0.02793  -0.0474   1.0000   0.0514
  -4.750  -0.3909   0.03567   0.02575  -0.0471   1.0000   0.0546
  -4.500  -0.3677   0.03357   0.02320  -0.0468   1.0000   0.0571
  -4.250  -0.3428   0.03155   0.02074  -0.0464   1.0000   0.0585
  -4.000  -0.3174   0.02986   0.01864  -0.0459   1.0000   0.0603
  -3.750  -0.2868   0.02845   0.01716  -0.0467   0.9973   0.0647
  -3.500  -0.2521   0.02737   0.01580  -0.0481   0.9930   0.0715
  -3.250  -0.2180   0.02639   0.01477  -0.0495   0.9883   0.0772
  -3.000  -0.1833   0.02572   0.01396  -0.0512   0.9832   0.0899
  -2.750  -0.1475   0.02494   0.01299  -0.0531   0.9780   0.1084
  -2.500  -0.1108   0.02357   0.01190  -0.0559   0.9736   0.1619
  -2.250  -0.0845   0.02143   0.01193  -0.0561   0.9696   0.6052
  -2.000  -0.0615   0.02135   0.01213  -0.0536   0.9636   0.7529
  -1.750  -0.0464   0.02103   0.01209  -0.0490   0.9559   0.8678
  -1.500   0.0069   0.02098   0.01177  -0.0538   0.9505   1.0000
  -1.250   0.0375   0.02113   0.01160  -0.0555   0.9417   1.0000
  -1.000   0.0774   0.02138   0.01152  -0.0588   0.9361   1.0000
  -0.750   0.1064   0.02159   0.01147  -0.0600   0.9271   1.0000
  -0.500   0.1453   0.02186   0.01150  -0.0629   0.9214   1.0000
  -0.250   0.1729   0.02212   0.01158  -0.0636   0.9123   1.0000
   0.000   0.2106   0.02239   0.01167  -0.0661   0.9065   1.0000
   0.250   0.2375   0.02269   0.01184  -0.0666   0.8974   1.0000
   0.500   0.2734   0.02297   0.01201  -0.0687   0.8914   1.0000
   0.750   0.3005   0.02329   0.01226  -0.0692   0.8824   1.0000
   1.000   0.3334   0.02360   0.01249  -0.0706   0.8758   1.0000
   1.500   0.3915   0.02426   0.01311  -0.0721   0.8599   1.0000
   1.750   0.4207   0.02461   0.01346  -0.0728   0.8521   1.0000
   2.000   0.4481   0.02498   0.01385  -0.0731   0.8439   1.0000
   2.250   0.4784   0.02531   0.01422  -0.0740   0.8367   1.0000
   2.500   0.5033   0.02574   0.01473  -0.0739   0.8277   1.0000
   2.750   0.5355   0.02599   0.01507  -0.0749   0.8210   1.0000
   3.000   0.5590   0.02640   0.01556  -0.0744   0.8104   1.0000
   3.250   0.5882   0.02659   0.01589  -0.0746   0.8008   1.0000
   3.500   0.6226   0.02651   0.01596  -0.0753   0.7915   1.0000
   3.750   0.6493   0.02658   0.01617  -0.0748   0.7787   1.0000
   4.000   0.6775   0.02652   0.01628  -0.0742   0.7654   1.0000
   4.250   0.7059   0.02643   0.01641  -0.0737   0.7520   1.0000
   4.500   0.7345   0.02629   0.01648  -0.0730   0.7383   1.0000
   4.750   0.7639   0.02601   0.01643  -0.0722   0.7232   1.0000
   5.000   0.7981   0.02517   0.01587  -0.0713   0.7039   1.0000
   5.250   0.8211   0.02449   0.01537  -0.0685   0.6709   1.0000
   5.500   0.8435   0.02379   0.01479  -0.0654   0.6268   1.0000
   5.750   0.8637   0.02342   0.01446  -0.0623   0.5697   1.0000
   6.000   0.8803   0.02346   0.01429  -0.0588   0.4706   1.0000
   6.250   0.8807   0.02521   0.01463  -0.0538   0.2677   1.0000
   6.500   0.8796   0.02775   0.01631  -0.0504   0.1660   1.0000
   6.750   0.8831   0.03005   0.01813  -0.0476   0.1251   1.0000
   7.000   0.8909   0.03191   0.01993  -0.0451   0.1000   1.0000
   7.250   0.9028   0.03351   0.02157  -0.0430   0.0852   1.0000
   7.500   0.9177   0.03485   0.02297  -0.0414   0.0740   1.0000
   7.750   0.9340   0.03624   0.02445  -0.0398   0.0664   1.0000
   8.000   0.9542   0.03784   0.02609  -0.0387   0.0621   1.0000
   8.250   0.9842   0.03952   0.02800  -0.0384   0.0566   1.0000
   8.500   1.0168   0.04179   0.03017  -0.0390   0.0516   1.0000
   8.750   1.0530   0.04443   0.03327  -0.0395   0.0494   1.0000
   9.000   1.0809   0.04751   0.03684  -0.0392   0.0478   1.0000
   9.250   1.1007   0.05078   0.04056  -0.0383   0.0465   1.0000
   9.500   1.1134   0.05391   0.04410  -0.0367   0.0449   1.0000
   9.750   1.1224   0.05686   0.04733  -0.0351   0.0432   1.0000
  10.000   1.1282   0.05995   0.05066  -0.0333   0.0417   1.0000
  10.250   1.1308   0.06359   0.05454  -0.0315   0.0407   1.0000
  10.500   1.1281   0.06746   0.05873  -0.0293   0.0404   1.0000
  10.750   1.1196   0.07114   0.06271  -0.0267   0.0403   1.0000
  11.000   1.1073   0.07482   0.06668  -0.0242   0.0402   1.0000
  11.250   1.0920   0.07858   0.07071  -0.0221   0.0403   1.0000
  11.500   1.0740   0.08258   0.07497  -0.0208   0.0404   1.0000
  11.750   1.0530   0.08701   0.07966  -0.0204   0.0406   1.0000
  12.000   1.0289   0.09226   0.08516  -0.0213   0.0409   1.0000
  12.250   1.0004   0.09893   0.09205  -0.0241   0.0414   1.0000
  12.500   0.9571   0.10982   0.10315  -0.0314   0.0427   1.0000
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