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NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-108 AIRFOIL (n64108-il)
Reynolds number: 200,000
Max Cl/Cd: 49.43 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64108-il-200000.txt
Download as CSV file: xf-n64108-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6101   0.08462   0.08122  -0.0095   1.0000   0.0399
  -8.500  -0.6168   0.07896   0.07562  -0.0147   1.0000   0.0402
  -8.250  -0.6282   0.07375   0.07040  -0.0193   1.0000   0.0401
  -8.000  -0.6344   0.06874   0.06530  -0.0225   1.0000   0.0410
  -7.750  -0.6370   0.06409   0.06042  -0.0253   1.0000   0.0429
  -7.500  -0.6359   0.06216   0.05797  -0.0261   1.0000   0.0443
  -7.250  -0.6373   0.05434   0.04997  -0.0272   1.0000   0.0454
  -7.000  -0.6238   0.05007   0.04581  -0.0274   1.0000   0.0471
  -6.750  -0.6093   0.04751   0.04322  -0.0274   1.0000   0.0513
  -6.250  -0.5815   0.04052   0.03570  -0.0272   1.0000   0.0620
  -5.750  -0.5462   0.03476   0.02942  -0.0264   1.0000   0.0753
  -5.500  -0.5277   0.03240   0.02671  -0.0258   1.0000   0.0871
  -5.250  -0.4958   0.02549   0.01875  -0.0225   1.0000   0.0414
  -5.000  -0.4728   0.02285   0.01576  -0.0214   1.0000   0.0405
  -4.750  -0.4493   0.02092   0.01353  -0.0203   1.0000   0.0412
  -4.500  -0.4259   0.01889   0.01126  -0.0190   1.0000   0.0404
  -4.250  -0.4031   0.01735   0.00956  -0.0177   1.0000   0.0409
  -4.000  -0.3812   0.01615   0.00826  -0.0164   1.0000   0.0424
  -3.750  -0.3607   0.01513   0.00715  -0.0150   1.0000   0.0455
  -3.500  -0.3420   0.01397   0.00605  -0.0135   1.0000   0.0495
  -3.250  -0.3226   0.01323   0.00529  -0.0121   1.0000   0.0538
  -3.000  -0.3033   0.01245   0.00449  -0.0109   1.0000   0.0608
  -2.750  -0.2831   0.01183   0.00392  -0.0099   1.0000   0.0801
  -2.500  -0.2690   0.00899   0.00339  -0.0089   1.0000   0.5905
  -2.250  -0.2455   0.00882   0.00360  -0.0078   0.9969   0.7112
  -2.000  -0.2087   0.00885   0.00370  -0.0094   0.9887   0.7643
  -1.750  -0.1759   0.00903   0.00403  -0.0094   0.9811   0.8233
  -1.500  -0.1477   0.00923   0.00431  -0.0082   0.9720   0.8658
  -1.250  -0.1121   0.00926   0.00428  -0.0095   0.9647   0.8841
  -1.000  -0.0733   0.00924   0.00421  -0.0116   0.9581   0.8963
  -0.750  -0.0373   0.00922   0.00415  -0.0131   0.9504   0.9086
  -0.500   0.0001   0.00917   0.00408  -0.0149   0.9432   0.9203
  -0.250   0.0343   0.00914   0.00401  -0.0160   0.9339   0.9325
   0.000   0.0722   0.00909   0.00395  -0.0178   0.9268   0.9438
   0.250   0.1092   0.00905   0.00391  -0.0196   0.9171   0.9546
   0.500   0.1507   0.00901   0.00387  -0.0223   0.9082   0.9628
   0.750   0.1917   0.00895   0.00383  -0.0250   0.9000   0.9714
   1.000   0.2343   0.00891   0.00381  -0.0281   0.8892   0.9791
   1.250   0.2765   0.00886   0.00383  -0.0312   0.8786   0.9870
   1.500   0.3174   0.00880   0.00381  -0.0340   0.8668   0.9962
   1.750   0.3429   0.00876   0.00380  -0.0337   0.8508   1.0000
   2.000   0.3561   0.00867   0.00366  -0.0303   0.8258   1.0000
   2.250   0.3679   0.00851   0.00336  -0.0262   0.7868   1.0000
   2.500   0.3838   0.00845   0.00321  -0.0232   0.7433   1.0000
   2.750   0.4048   0.00852   0.00325  -0.0216   0.7144   1.0000
   3.000   0.4261   0.00862   0.00326  -0.0200   0.6687   1.0000
   3.250   0.4445   0.00901   0.00321  -0.0176   0.5500   1.0000
   3.500   0.4487   0.01222   0.00406  -0.0148   0.0841   1.0000
   3.750   0.4717   0.01319   0.00499  -0.0141   0.0608   1.0000
   4.000   0.4951   0.01412   0.00597  -0.0133   0.0527   1.0000
   4.250   0.5169   0.01546   0.00723  -0.0125   0.0457   1.0000
   4.500   0.5417   0.01640   0.00825  -0.0118   0.0427   1.0000
   4.750   0.5667   0.01768   0.00958  -0.0111   0.0407   1.0000
   5.000   0.5926   0.01922   0.01123  -0.0104   0.0395   1.0000
   5.250   0.6191   0.02099   0.01319  -0.0098   0.0388   1.0000
   5.500   0.6435   0.02287   0.01512  -0.0095   0.0353   1.0000
   5.750   0.6694   0.02506   0.01762  -0.0087   0.0358   1.0000
   6.000   0.6941   0.02992   0.02325  -0.0068   0.0436   1.0000
   6.250   0.7222   0.03732   0.03184  -0.0032   0.0804   1.0000
   6.500   0.7421   0.03999   0.03454  -0.0028   0.0745   1.0000
   6.750   0.7560   0.04253   0.03747  -0.0020   0.0632   1.0000
   7.000   0.7745   0.04726   0.04193  -0.0026   0.0598   1.0000
   7.250   0.7800   0.04950   0.04504  -0.0007   0.0522   1.0000
   7.500   0.7920   0.05270   0.04841  -0.0003   0.0495   1.0000
   7.750   0.8052   0.05654   0.05220  -0.0003   0.0477   1.0000
   8.000   0.8035   0.06588   0.06156  -0.0012   0.0461   1.0000
   8.250   0.8029   0.06814   0.06421  -0.0003   0.0457   1.0000
   8.500   0.7895   0.07076   0.06731  -0.0004   0.0434   1.0000
   8.750   0.7776   0.07513   0.07182  -0.0013   0.0428   1.0000
   9.000   0.7610   0.07975   0.07650  -0.0033   0.0427   1.0000
   9.250   0.7463   0.08573   0.08250  -0.0080   0.0429   1.0000
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