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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 50,000
Max Cl/Cd: 32.93 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a210-il-50000-n5.txt
Download as CSV file: xf-naca64a210-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5480   0.09764   0.09053  -0.0264   1.0000   0.0516
  -9.500  -0.5503   0.09248   0.08542  -0.0294   1.0000   0.0509
  -9.250  -0.5547   0.08677   0.07976  -0.0335   1.0000   0.0502
  -9.000  -0.5631   0.08104   0.07407  -0.0378   1.0000   0.0495
  -8.750  -0.5750   0.07614   0.06918  -0.0405   1.0000   0.0488
  -8.500  -0.5846   0.07147   0.06445  -0.0423   1.0000   0.0484
  -8.250  -0.5918   0.06708   0.05994  -0.0433   1.0000   0.0484
  -8.000  -0.5961   0.06297   0.05565  -0.0435   1.0000   0.0487
  -7.750  -0.5977   0.05908   0.05153  -0.0431   1.0000   0.0492
  -7.500  -0.5968   0.05536   0.04752  -0.0423   1.0000   0.0497
  -7.250  -0.5933   0.05179   0.04357  -0.0410   1.0000   0.0501
  -7.000  -0.5870   0.04835   0.03977  -0.0395   1.0000   0.0501
  -6.750  -0.5780   0.04511   0.03614  -0.0379   1.0000   0.0502
  -6.500  -0.5665   0.04209   0.03269  -0.0362   1.0000   0.0506
  -6.250  -0.5525   0.03930   0.02946  -0.0345   1.0000   0.0512
  -6.000  -0.5363   0.03684   0.02652  -0.0329   1.0000   0.0526
  -5.750  -0.5187   0.03474   0.02393  -0.0313   1.0000   0.0551
  -5.500  -0.5003   0.03269   0.02180  -0.0302   1.0000   0.0580
  -5.250  -0.4798   0.03090   0.01974  -0.0289   1.0000   0.0601
  -5.000  -0.4581   0.02928   0.01790  -0.0276   1.0000   0.0625
  -4.750  -0.4362   0.02793   0.01630  -0.0262   1.0000   0.0662
  -4.500  -0.4161   0.02668   0.01504  -0.0249   1.0000   0.0722
  -4.250  -0.3959   0.02564   0.01386  -0.0234   1.0000   0.0787
  -4.000  -0.3766   0.02454   0.01269  -0.0219   1.0000   0.0851
  -3.750  -0.3571   0.02359   0.01166  -0.0209   1.0000   0.0987
  -3.500  -0.3367   0.02252   0.01062  -0.0201   1.0000   0.1187
  -3.250  -0.3167   0.02093   0.00952  -0.0198   1.0000   0.1854
  -3.000  -0.3056   0.01878   0.00944  -0.0169   1.0000   0.5728
  -2.750  -0.2941   0.01872   0.00969  -0.0124   1.0000   0.7000
  -2.500  -0.2866   0.01878   0.00995  -0.0063   1.0000   0.7960
  -2.250  -0.2714   0.01898   0.01029  -0.0004   1.0000   0.8917
  -2.000  -0.2249   0.01914   0.01014  -0.0034   1.0000   0.9366
  -1.750  -0.1816   0.01913   0.00984  -0.0074   1.0000   0.9598
  -1.500  -0.1306   0.01917   0.00956  -0.0132   0.9961   0.9806
  -1.250  -0.0772   0.01922   0.00934  -0.0197   0.9897   1.0000
  -1.000  -0.0434   0.01924   0.00915  -0.0227   0.9789   1.0000
  -0.750  -0.0100   0.01931   0.00904  -0.0253   0.9684   1.0000
  -0.500   0.0236   0.01943   0.00900  -0.0278   0.9584   1.0000
  -0.250   0.0611   0.01960   0.00902  -0.0308   0.9501   1.0000
   0.000   0.0921   0.01976   0.00907  -0.0324   0.9394   1.0000
   0.250   0.1251   0.01996   0.00918  -0.0343   0.9300   1.0000
   0.500   0.1632   0.02017   0.00933  -0.0371   0.9222   1.0000
   0.750   0.1927   0.02040   0.00952  -0.0381   0.9119   1.0000
   1.000   0.2261   0.02064   0.00974  -0.0399   0.9031   1.0000
   1.250   0.2602   0.02088   0.00998  -0.0416   0.8947   1.0000
   1.500   0.2882   0.02115   0.01029  -0.0422   0.8844   1.0000
   1.750   0.3210   0.02140   0.01059  -0.0436   0.8763   1.0000
   2.000   0.3503   0.02168   0.01093  -0.0443   0.8666   1.0000
   2.250   0.3771   0.02201   0.01135  -0.0445   0.8565   1.0000
   2.500   0.4104   0.02224   0.01170  -0.0457   0.8486   1.0000
   2.750   0.4365   0.02258   0.01216  -0.0458   0.8379   1.0000
   3.000   0.4626   0.02292   0.01267  -0.0457   0.8270   1.0000
   3.250   0.4921   0.02318   0.01309  -0.0461   0.8169   1.0000
   3.500   0.5238   0.02333   0.01345  -0.0466   0.8068   1.0000
   3.750   0.5505   0.02354   0.01387  -0.0462   0.7936   1.0000
   4.000   0.5793   0.02358   0.01419  -0.0458   0.7792   1.0000
   4.250   0.6067   0.02326   0.01411  -0.0442   0.7564   1.0000
   4.500   0.6366   0.02177   0.01277  -0.0405   0.7097   1.0000
   4.750   0.6573   0.02076   0.01175  -0.0358   0.6421   1.0000
   5.000   0.6750   0.02050   0.01140  -0.0319   0.5533   1.0000
   5.250   0.6831   0.02147   0.01112  -0.0269   0.3212   1.0000
   5.500   0.6838   0.02430   0.01260  -0.0238   0.1570   1.0000
   5.750   0.6954   0.02626   0.01418  -0.0218   0.1150   1.0000
   6.000   0.7104   0.02784   0.01567  -0.0201   0.0945   1.0000
   6.250   0.7275   0.02931   0.01717  -0.0186   0.0821   1.0000
   6.500   0.7478   0.03084   0.01882  -0.0174   0.0744   1.0000
   6.750   0.7705   0.03232   0.02033  -0.0166   0.0662   1.0000
   7.000   0.7995   0.03407   0.02225  -0.0161   0.0612   1.0000
   7.250   0.8299   0.03609   0.02450  -0.0159   0.0576   1.0000
   7.500   0.8557   0.03819   0.02671  -0.0157   0.0540   1.0000
   7.750   0.8794   0.04070   0.02951  -0.0151   0.0508   1.0000
   8.000   0.9007   0.04338   0.03269  -0.0141   0.0488   1.0000
   8.250   0.9189   0.04645   0.03623  -0.0129   0.0477   1.0000
   8.500   0.9328   0.04975   0.04000  -0.0114   0.0470   1.0000
   8.750   0.9424   0.05326   0.04397  -0.0097   0.0465   1.0000
   9.000   0.9477   0.05694   0.04809  -0.0079   0.0462   1.0000
   9.250   0.9488   0.06066   0.05221  -0.0060   0.0458   1.0000
   9.500   0.9459   0.06435   0.05625  -0.0042   0.0452   1.0000
   9.750   0.9393   0.06805   0.06024  -0.0025   0.0446   1.0000
  10.000   0.9279   0.07174   0.06417  -0.0009   0.0442   1.0000
  10.250   0.9113   0.07565   0.06829   0.0004   0.0442   1.0000
  10.500   0.8906   0.08030   0.07312   0.0004   0.0445   1.0000
  10.750   0.8676   0.08591   0.07888  -0.0013   0.0452   1.0000
  11.000   0.8437   0.09273   0.08581  -0.0050   0.0461   1.0000
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