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NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-108 AIRFOIL (n64108-il)
Reynolds number: 1,000,000
Max Cl/Cd: 65.29 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64108-il-1000000-n5.txt
Download as CSV file: xf-n64108-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-108 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6559   0.11117   0.10955   0.0095   1.0000   0.0031
  -9.750  -0.9314   0.02430   0.02090  -0.0230   1.0000   0.0028
  -9.500  -0.9156   0.02171   0.01796  -0.0223   1.0000   0.0028
  -9.250  -0.8951   0.02023   0.01627  -0.0218   1.0000   0.0029
  -9.000  -0.8777   0.01777   0.01344  -0.0210   1.0000   0.0032
  -8.750  -0.8539   0.01703   0.01262  -0.0207   1.0000   0.0035
  -8.500  -0.8294   0.01649   0.01201  -0.0205   1.0000   0.0038
  -8.250  -0.8051   0.01581   0.01124  -0.0202   1.0000   0.0040
  -8.000  -0.7805   0.01520   0.01051  -0.0200   1.0000   0.0043
  -7.750  -0.7564   0.01440   0.00960  -0.0196   1.0000   0.0046
  -7.500  -0.7320   0.01368   0.00876  -0.0193   1.0000   0.0049
  -7.250  -0.7072   0.01308   0.00807  -0.0190   1.0000   0.0051
  -7.000  -0.6825   0.01246   0.00736  -0.0186   1.0000   0.0053
  -6.750  -0.6581   0.01180   0.00664  -0.0183   1.0000   0.0060
  -6.500  -0.6274   0.01152   0.00635  -0.0192   0.9908   0.0065
  -6.250  -0.5944   0.01120   0.00598  -0.0206   0.9791   0.0073
  -6.000  -0.5617   0.01092   0.00566  -0.0219   0.9668   0.0081
  -5.750  -0.5315   0.01065   0.00534  -0.0226   0.9528   0.0086
  -5.500  -0.5045   0.01040   0.00503  -0.0226   0.9375   0.0088
  -5.250  -0.4803   0.00965   0.00412  -0.0220   0.9223   0.0100
  -5.000  -0.4547   0.00935   0.00376  -0.0216   0.9085   0.0109
  -4.750  -0.4285   0.00916   0.00350  -0.0213   0.8955   0.0118
  -4.250  -0.3757   0.00869   0.00288  -0.0208   0.8709   0.0131
  -4.000  -0.3489   0.00846   0.00257  -0.0207   0.8594   0.0136
  -3.750  -0.3219   0.00829   0.00233  -0.0206   0.8483   0.0143
  -3.500  -0.2948   0.00807   0.00202  -0.0204   0.8376   0.0156
  -3.250  -0.2677   0.00787   0.00179  -0.0203   0.8269   0.0199
  -3.000  -0.2402   0.00774   0.00163  -0.0203   0.8166   0.0234
  -2.750  -0.2126   0.00762   0.00147  -0.0203   0.8067   0.0276
  -2.500  -0.1851   0.00750   0.00132  -0.0203   0.7965   0.0342
  -2.250  -0.1576   0.00737   0.00120  -0.0203   0.7860   0.0458
  -2.000  -0.1302   0.00714   0.00107  -0.0203   0.7755   0.0836
  -1.750  -0.1032   0.00674   0.00092  -0.0204   0.7659   0.1676
  -1.500  -0.0771   0.00605   0.00073  -0.0206   0.7562   0.3298
  -1.250  -0.0507   0.00551   0.00061  -0.0207   0.7460   0.4667
  -1.000  -0.0237   0.00520   0.00058  -0.0208   0.7358   0.5562
  -0.750   0.0035   0.00502   0.00057  -0.0207   0.7261   0.6191
  -0.500   0.0310   0.00492   0.00056  -0.0207   0.7167   0.6577
  -0.250   0.0588   0.00486   0.00057  -0.0207   0.7076   0.6854
   0.000   0.0869   0.00486   0.00057  -0.0207   0.6982   0.6982
   0.250   0.1147   0.00489   0.00058  -0.0207   0.6799   0.7084
   0.500   0.1422   0.00497   0.00058  -0.0207   0.6527   0.7178
   0.750   0.1699   0.00504   0.00060  -0.0207   0.6314   0.7277
   1.000   0.1974   0.00513   0.00063  -0.0206   0.6020   0.7379
   1.250   0.2241   0.00535   0.00067  -0.0205   0.5437   0.7481
   1.500   0.2507   0.00563   0.00075  -0.0204   0.4771   0.7584
   1.750   0.2753   0.00635   0.00093  -0.0202   0.3228   0.7686
   2.000   0.2999   0.00712   0.00118  -0.0200   0.1703   0.7786
   2.250   0.3262   0.00752   0.00136  -0.0200   0.0980   0.7893
   2.500   0.3528   0.00784   0.00155  -0.0199   0.0519   0.8004
   2.750   0.3800   0.00801   0.00170  -0.0199   0.0368   0.8114
   3.000   0.4072   0.00816   0.00185  -0.0198   0.0303   0.8220
   3.250   0.4344   0.00829   0.00203  -0.0197   0.0260   0.8329
   3.500   0.4614   0.00844   0.00222  -0.0196   0.0212   0.8443
   3.750   0.4881   0.00866   0.00246  -0.0194   0.0163   0.8561
   4.000   0.5147   0.00883   0.00269  -0.0192   0.0153   0.8684
   4.250   0.5410   0.00902   0.00295  -0.0189   0.0143   0.8813
   4.500   0.5669   0.00923   0.00323  -0.0185   0.0135   0.8951
   4.750   0.5923   0.00946   0.00354  -0.0181   0.0127   0.9096
   5.000   0.6172   0.00973   0.00387  -0.0175   0.0117   0.9254
   5.250   0.6407   0.01020   0.00446  -0.0167   0.0102   0.9435
   5.500   0.6668   0.01063   0.00499  -0.0164   0.0098   0.9659
   5.750   0.6987   0.01099   0.00541  -0.0176   0.0095   1.0000
   6.000   0.7251   0.01132   0.00579  -0.0175   0.0090   1.0000
   6.250   0.7516   0.01163   0.00613  -0.0174   0.0083   1.0000
   6.500   0.7777   0.01201   0.00655  -0.0173   0.0077   1.0000
   6.750   0.8038   0.01237   0.00693  -0.0172   0.0072   1.0000
   7.000   0.8298   0.01271   0.00729  -0.0171   0.0067   1.0000
   7.250   0.8537   0.01354   0.00820  -0.0167   0.0060   1.0000
   7.500   0.8786   0.01411   0.00884  -0.0164   0.0057   1.0000
   7.750   0.9041   0.01454   0.00937  -0.0163   0.0054   1.0000
   8.000   0.9293   0.01498   0.00987  -0.0161   0.0050   1.0000
   8.250   0.9547   0.01539   0.01031  -0.0159   0.0046   1.0000
   8.500   0.9797   0.01582   0.01079  -0.0157   0.0042   1.0000
   8.750   1.0045   0.01629   0.01130  -0.0155   0.0039   1.0000
   9.000   1.0282   0.01699   0.01207  -0.0152   0.0036   1.0000
   9.250   1.0489   0.01834   0.01360  -0.0145   0.0033   1.0000
   9.500   1.0714   0.01925   0.01465  -0.0140   0.0032   1.0000
   9.750   1.0925   0.02041   0.01599  -0.0134   0.0031   1.0000
  10.000   1.1131   0.02161   0.01739  -0.0127   0.0029   1.0000
  10.250   1.1317   0.02315   0.01915  -0.0119   0.0028   1.0000
  10.500   1.1492   0.02478   0.02099  -0.0111   0.0027   1.0000
  10.750   1.1651   0.02659   0.02303  -0.0101   0.0026   1.0000
  11.000   1.1767   0.02904   0.02577  -0.0088   0.0025   1.0000
  11.250   1.1871   0.03142   0.02841  -0.0076   0.0024   1.0000
  11.500   1.1804   0.03641   0.03385  -0.0053   0.0023   1.0000
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