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NACA 0008 (naca0008-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0008 (naca0008-il)
Reynolds number: 200,000
Max Cl/Cd: 38.52 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0008-il-200000-n5.txt
Download as CSV file: xf-naca0008-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7808   0.09050   0.08710   0.0095   1.0000   0.0131
 -10.500  -0.8455   0.06451   0.06109  -0.0106   1.0000   0.0119
 -10.250  -0.8812   0.05527   0.05156  -0.0172   1.0000   0.0116
 -10.000  -0.9046   0.04947   0.04544  -0.0171   1.0000   0.0116
  -9.750  -0.9151   0.04434   0.03990  -0.0165   1.0000   0.0118
  -9.500  -0.9164   0.03998   0.03510  -0.0153   1.0000   0.0120
  -9.250  -0.9110   0.03627   0.03095  -0.0141   1.0000   0.0125
  -9.000  -0.8996   0.03341   0.02768  -0.0130   1.0000   0.0133
  -8.750  -0.8848   0.03091   0.02476  -0.0118   1.0000   0.0142
  -8.500  -0.8675   0.02872   0.02215  -0.0108   1.0000   0.0149
  -8.250  -0.8518   0.02600   0.01912  -0.0096   1.0000   0.0159
  -8.000  -0.8311   0.02469   0.01762  -0.0089   1.0000   0.0169
  -7.750  -0.8093   0.02357   0.01634  -0.0082   1.0000   0.0182
  -7.500  -0.7865   0.02256   0.01514  -0.0075   1.0000   0.0203
  -7.250  -0.7634   0.02146   0.01380  -0.0068   1.0000   0.0224
  -7.000  -0.7418   0.02002   0.01222  -0.0059   1.0000   0.0242
  -6.750  -0.7186   0.01924   0.01140  -0.0053   1.0000   0.0270
  -6.500  -0.6946   0.01854   0.01058  -0.0047   1.0000   0.0304
  -6.250  -0.6704   0.01788   0.00972  -0.0041   1.0000   0.0328
  -6.000  -0.6482   0.01686   0.00870  -0.0034   1.0000   0.0367
  -5.750  -0.6241   0.01626   0.00803  -0.0028   1.0000   0.0401
  -5.500  -0.5996   0.01576   0.00742  -0.0022   1.0000   0.0431
  -5.250  -0.5767   0.01497   0.00662  -0.0014   1.0000   0.0468
  -5.000  -0.5525   0.01445   0.00604  -0.0008   1.0000   0.0508
  -4.750  -0.5281   0.01400   0.00550  -0.0002   1.0000   0.0549
  -4.500  -0.5042   0.01345   0.00495   0.0005   1.0000   0.0603
  -4.250  -0.4798   0.01303   0.00450   0.0012   1.0000   0.0690
  -4.000  -0.4559   0.01253   0.00407   0.0018   1.0000   0.0871
  -3.750  -0.4322   0.01202   0.00371   0.0025   1.0000   0.1203
  -3.500  -0.4086   0.01152   0.00340   0.0031   1.0000   0.1665
  -3.250  -0.3853   0.01100   0.00314   0.0037   1.0000   0.2255
  -3.000  -0.3621   0.01048   0.00291   0.0043   1.0000   0.2977
  -2.750  -0.3390   0.00999   0.00275   0.0050   1.0000   0.3732
  -2.500  -0.3159   0.00954   0.00262   0.0058   1.0000   0.4505
  -2.250  -0.2930   0.00912   0.00252   0.0066   1.0000   0.5291
  -2.000  -0.2701   0.00875   0.00249   0.0077   1.0000   0.6060
  -1.750  -0.2472   0.00845   0.00248   0.0089   1.0000   0.6771
  -1.500  -0.2242   0.00823   0.00251   0.0101   1.0000   0.7387
  -1.250  -0.1962   0.00809   0.00255   0.0104   0.9971   0.7931
  -1.000  -0.1604   0.00803   0.00262   0.0091   0.9896   0.8398
  -0.750  -0.1227   0.00803   0.00267   0.0074   0.9817   0.8787
  -0.500  -0.0830   0.00805   0.00272   0.0053   0.9728   0.9092
  -0.250  -0.0415   0.00807   0.00274   0.0027   0.9623   0.9319
   0.000   0.0000   0.00807   0.00275   0.0000   0.9492   0.9492
   0.250   0.0415   0.00807   0.00274  -0.0027   0.9319   0.9623
   0.500   0.0830   0.00805   0.00272  -0.0053   0.9092   0.9728
   0.750   0.1227   0.00803   0.00267  -0.0074   0.8787   0.9817
   1.000   0.1604   0.00803   0.00261  -0.0091   0.8398   0.9896
   1.250   0.1962   0.00809   0.00255  -0.0104   0.7931   0.9971
   1.500   0.2242   0.00823   0.00250  -0.0101   0.7387   1.0000
   1.750   0.2472   0.00845   0.00248  -0.0089   0.6773   1.0000
   2.000   0.2702   0.00875   0.00249  -0.0077   0.6061   1.0000
   2.250   0.2930   0.00912   0.00252  -0.0066   0.5291   1.0000
   2.500   0.3159   0.00954   0.00262  -0.0058   0.4504   1.0000
   2.750   0.3390   0.00999   0.00275  -0.0050   0.3733   1.0000
   3.000   0.3621   0.01048   0.00291  -0.0043   0.2976   1.0000
   3.250   0.3853   0.01101   0.00314  -0.0037   0.2253   1.0000
   3.500   0.4087   0.01152   0.00340  -0.0031   0.1665   1.0000
   3.750   0.4322   0.01202   0.00371  -0.0025   0.1203   1.0000
   4.000   0.4559   0.01253   0.00407  -0.0018   0.0872   1.0000
   4.250   0.4798   0.01303   0.00450  -0.0012   0.0690   1.0000
   4.500   0.5042   0.01345   0.00495  -0.0005   0.0603   1.0000
   4.750   0.5282   0.01400   0.00550   0.0002   0.0549   1.0000
   5.000   0.5526   0.01445   0.00604   0.0008   0.0508   1.0000
   5.250   0.5767   0.01497   0.00662   0.0014   0.0468   1.0000
   5.500   0.5997   0.01576   0.00742   0.0022   0.0431   1.0000
   5.750   0.6241   0.01626   0.00803   0.0028   0.0401   1.0000
   6.000   0.6482   0.01686   0.00870   0.0034   0.0367   1.0000
   6.250   0.6703   0.01788   0.00973   0.0041   0.0328   1.0000
   6.500   0.6946   0.01854   0.01057   0.0047   0.0304   1.0000
   6.750   0.7186   0.01924   0.01139   0.0053   0.0270   1.0000
   7.000   0.7418   0.02002   0.01222   0.0059   0.0242   1.0000
   7.250   0.7634   0.02146   0.01380   0.0068   0.0224   1.0000
   7.500   0.7865   0.02256   0.01514   0.0075   0.0203   1.0000
   7.750   0.8092   0.02356   0.01633   0.0082   0.0182   1.0000
   8.000   0.8311   0.02469   0.01762   0.0089   0.0169   1.0000
   8.250   0.8518   0.02599   0.01912   0.0096   0.0159   1.0000
   8.500   0.8675   0.02872   0.02215   0.0108   0.0149   1.0000
   8.750   0.8848   0.03091   0.02476   0.0118   0.0142   1.0000
   9.000   0.8996   0.03341   0.02768   0.0130   0.0133   1.0000
   9.250   0.9111   0.03626   0.03094   0.0141   0.0125   1.0000
   9.500   0.9164   0.03998   0.03511   0.0153   0.0120   1.0000
   9.750   0.9152   0.04433   0.03989   0.0164   0.0118   1.0000
  10.000   0.9047   0.04949   0.04545   0.0171   0.0116   1.0000
  10.250   0.8812   0.05531   0.05160   0.0171   0.0116   1.0000
  10.500   0.8450   0.06474   0.06132   0.0103   0.0120   1.0000
  10.750   0.7811   0.09065   0.08725  -0.0097   0.0131   1.0000
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