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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 50,000
Max Cl/Cd: 33.69 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a210-il-50000.txt
Download as CSV file: xf-naca64a210-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4979   0.10625   0.09924  -0.0007   1.0000   0.3256
  -8.750  -0.4941   0.10322   0.09625  -0.0002   1.0000   0.3436
  -8.500  -0.5080   0.10166   0.09480  -0.0001   1.0000   0.3619
  -8.250  -0.4823   0.09667   0.08977   0.0012   1.0000   0.3802
  -8.000  -0.4737   0.09351   0.08664   0.0022   1.0000   0.4006
  -7.750  -0.4697   0.09052   0.08369   0.0032   1.0000   0.4220
  -7.500  -0.4739   0.08871   0.08197   0.0050   1.0000   0.4476
  -7.250  -0.4478   0.08399   0.07721   0.0056   1.0000   0.4669
  -6.500  -0.5729   0.05446   0.04726  -0.0358   1.0000   0.1680
  -6.250  -0.5663   0.04918   0.04123  -0.0359   1.0000   0.1437
  -6.000  -0.5547   0.04516   0.03648  -0.0346   1.0000   0.1312
  -5.750  -0.5391   0.04157   0.03264  -0.0333   1.0000   0.1264
  -5.500  -0.5226   0.03843   0.02892  -0.0319   1.0000   0.1229
  -5.250  -0.5042   0.03590   0.02601  -0.0305   1.0000   0.1246
  -5.000  -0.4837   0.03353   0.02323  -0.0292   1.0000   0.1262
  -4.750  -0.4610   0.03127   0.02056  -0.0279   1.0000   0.1269
  -4.500  -0.4370   0.02929   0.01822  -0.0267   1.0000   0.1294
  -4.250  -0.4132   0.02748   0.01628  -0.0256   1.0000   0.1375
  -4.000  -0.3886   0.02593   0.01460  -0.0244   1.0000   0.1486
  -3.750  -0.3643   0.02443   0.01313  -0.0230   1.0000   0.1628
  -3.500  -0.3417   0.02289   0.01180  -0.0219   1.0000   0.1935
  -3.250  -0.3217   0.02027   0.01013  -0.0210   1.0000   0.2938
  -3.000  -0.0733   0.02109   0.01165  -0.0395   1.0000   1.0000
  -2.750  -0.0707   0.02070   0.01119  -0.0372   1.0000   1.0000
  -2.500  -0.0714   0.02037   0.01081  -0.0342   1.0000   1.0000
  -2.250  -0.0760   0.02008   0.01049  -0.0307   1.0000   1.0000
  -2.000  -0.0844   0.01982   0.01019  -0.0265   1.0000   1.0000
  -1.750  -0.0959   0.01954   0.00990  -0.0219   1.0000   1.0000
  -1.500  -0.1089   0.01925   0.00958  -0.0170   1.0000   1.0000
  -1.250  -0.1179   0.01900   0.00926  -0.0127   1.0000   1.0000
  -1.000  -0.1143   0.01892   0.00903  -0.0103   1.0000   1.0000
  -0.750  -0.1015   0.01900   0.00891  -0.0093   1.0000   1.0000
  -0.500  -0.0847   0.01918   0.00891  -0.0089   1.0000   1.0000
  -0.250  -0.0662   0.01944   0.00901  -0.0087   1.0000   1.0000
   0.000  -0.0468   0.01976   0.00918  -0.0086   1.0000   1.0000
   0.250  -0.0269   0.02012   0.00942  -0.0086   1.0000   1.0000
   0.500  -0.0068   0.02054   0.00972  -0.0086   1.0000   1.0000
   0.750   0.0134   0.02099   0.01008  -0.0087   1.0000   1.0000
   1.000   0.0336   0.02149   0.01051  -0.0088   1.0000   1.0000
   1.250   0.0538   0.02203   0.01100  -0.0089   1.0000   1.0000
   1.500   0.0739   0.02262   0.01154  -0.0091   1.0000   1.0000
   1.750   0.0939   0.02324   0.01214  -0.0093   1.0000   1.0000
   2.000   0.1138   0.02391   0.01279  -0.0095   1.0000   1.0000
   2.250   0.1335   0.02462   0.01351  -0.0098   1.0000   1.0000
   2.500   0.1530   0.02538   0.01430  -0.0100   1.0000   1.0000
   2.750   0.1748   0.02622   0.01518  -0.0108   0.9988   1.0000
   3.000   0.2194   0.02753   0.01659  -0.0160   0.9871   1.0000
   3.250   0.2620   0.02881   0.01800  -0.0206   0.9747   1.0000
   3.500   0.3030   0.03006   0.01943  -0.0248   0.9612   1.0000
   3.750   0.3437   0.03129   0.02084  -0.0288   0.9464   1.0000
   4.000   0.3858   0.03250   0.02228  -0.0329   0.9302   1.0000
   4.250   0.4340   0.03371   0.02381  -0.0376   0.9122   1.0000
   4.500   0.4668   0.03461   0.02497  -0.0394   0.8907   1.0000
   4.750   0.5162   0.03526   0.02605  -0.0430   0.8631   1.0000
   5.000   0.6768   0.02660   0.01873  -0.0461   0.7524   1.0000
   5.250   0.7059   0.02095   0.01321  -0.0320   0.5801   1.0000
   5.500   0.6897   0.02423   0.01353  -0.0224   0.2324   1.0000
   5.750   0.7033   0.02685   0.01554  -0.0200   0.1777   1.0000
   6.000   0.7329   0.02907   0.01756  -0.0193   0.1496   1.0000
   6.250   0.7670   0.03131   0.01967  -0.0194   0.1310   1.0000
   6.500   0.8018   0.03391   0.02248  -0.0195   0.1223   1.0000
   6.750   0.8324   0.03666   0.02539  -0.0192   0.1170   1.0000
   7.000   0.8570   0.03967   0.02871  -0.0184   0.1123   1.0000
   7.250   0.8781   0.04259   0.03216  -0.0170   0.1098   1.0000
   7.500   0.8977   0.04613   0.03618  -0.0156   0.1105   1.0000
   7.750   0.9145   0.05003   0.04055  -0.0142   0.1123   1.0000
   8.000   0.9335   0.05481   0.04549  -0.0134   0.1144   1.0000
   8.250   0.9281   0.05852   0.05037  -0.0101   0.1220   1.0000
   8.500   0.9356   0.06339   0.05552  -0.0089   0.1260   1.0000
   8.750   0.9227   0.06863   0.06142  -0.0073   0.1358   1.0000
   9.000   0.8305   0.06359   0.05699   0.0016   0.1387   1.0000
   9.250   0.8041   0.06896   0.06254   0.0030   0.1450   1.0000
   9.500   0.7598   0.07468   0.06833   0.0031   0.1471   1.0000
   9.750   0.7207   0.08202   0.07569   0.0003   0.1510   1.0000
  10.000   0.6759   0.09245   0.08607  -0.0065   0.1615   1.0000
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