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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 500,000
Max Cl/Cd: 66.64 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1408-il-500000.txt
Download as CSV file: xf-naca1408-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.8112   0.04158   0.03856  -0.0342   1.0000   0.0140
  -9.250  -0.8175   0.03542   0.03188  -0.0338   1.0000   0.0140
  -9.000  -0.8109   0.03152   0.02761  -0.0331   1.0000   0.0143
  -8.750  -0.7946   0.02964   0.02554  -0.0324   1.0000   0.0147
  -8.500  -0.7748   0.02857   0.02434  -0.0319   1.0000   0.0153
  -8.250  -0.7550   0.02731   0.02292  -0.0313   1.0000   0.0161
  -8.000  -0.7376   0.02501   0.02029  -0.0302   1.0000   0.0170
  -7.750  -0.7191   0.02284   0.01775  -0.0290   1.0000   0.0177
  -7.500  -0.6978   0.02159   0.01623  -0.0280   1.0000   0.0182
  -7.250  -0.6810   0.01859   0.01291  -0.0266   1.0000   0.0192
  -7.000  -0.6587   0.01781   0.01208  -0.0258   1.0000   0.0202
  -6.750  -0.6357   0.01725   0.01144  -0.0250   1.0000   0.0214
  -6.500  -0.6124   0.01671   0.01081  -0.0242   1.0000   0.0230
  -6.250  -0.5887   0.01631   0.01030  -0.0233   1.0000   0.0242
  -6.000  -0.5685   0.01445   0.00829  -0.0221   1.0000   0.0260
  -5.750  -0.5458   0.01384   0.00766  -0.0212   1.0000   0.0278
  -5.500  -0.5225   0.01342   0.00720  -0.0203   1.0000   0.0300
  -5.250  -0.4989   0.01312   0.00684  -0.0195   1.0000   0.0320
  -5.000  -0.4771   0.01209   0.00572  -0.0184   1.0000   0.0344
  -4.750  -0.4542   0.01152   0.00513  -0.0175   1.0000   0.0371
  -4.500  -0.4306   0.01119   0.00478  -0.0167   1.0000   0.0400
  -4.250  -0.4068   0.01090   0.00445  -0.0160   1.0000   0.0422
  -4.000  -0.3832   0.01035   0.00385  -0.0152   1.0000   0.0453
  -3.750  -0.3590   0.01001   0.00351  -0.0146   1.0000   0.0495
  -3.500  -0.3345   0.00978   0.00326  -0.0140   1.0000   0.0531
  -3.250  -0.3038   0.00943   0.00293  -0.0148   0.9988   0.0612
  -3.000  -0.2666   0.00892   0.00261  -0.0169   0.9961   0.1000
  -2.750  -0.2300   0.00834   0.00240  -0.0192   0.9936   0.1870
  -2.500  -0.1945   0.00787   0.00226  -0.0212   0.9896   0.2690
  -2.250  -0.1578   0.00741   0.00213  -0.0234   0.9862   0.3588
  -2.000  -0.1200   0.00695   0.00203  -0.0258   0.9834   0.4569
  -1.750  -0.0870   0.00646   0.00195  -0.0271   0.9778   0.5666
  -1.500  -0.0521   0.00603   0.00188  -0.0286   0.9732   0.6680
  -1.250  -0.0206   0.00564   0.00185  -0.0291   0.9672   0.7661
  -1.000   0.0066   0.00533   0.00187  -0.0283   0.9587   0.8600
  -0.750   0.0343   0.00522   0.00187  -0.0276   0.9486   0.9114
  -0.500   0.0674   0.00519   0.00186  -0.0281   0.9390   0.9513
  -0.250   0.1048   0.00517   0.00183  -0.0296   0.9273   0.9732
   0.000   0.1433   0.00517   0.00178  -0.0316   0.9128   0.9862
   0.250   0.1842   0.00517   0.00173  -0.0342   0.8959   0.9956
   0.500   0.2182   0.00517   0.00166  -0.0354   0.8740   1.0000
   0.750   0.2430   0.00520   0.00159  -0.0345   0.8478   1.0000
   1.000   0.2679   0.00526   0.00154  -0.0337   0.8179   1.0000
   1.250   0.2929   0.00535   0.00151  -0.0329   0.7864   1.0000
   1.500   0.3177   0.00549   0.00150  -0.0321   0.7506   1.0000
   1.750   0.3414   0.00572   0.00149  -0.0310   0.6942   1.0000
   2.000   0.3654   0.00597   0.00151  -0.0301   0.6399   1.0000
   2.250   0.3901   0.00619   0.00157  -0.0294   0.5979   1.0000
   2.500   0.4147   0.00643   0.00165  -0.0287   0.5556   1.0000
   2.750   0.4393   0.00671   0.00175  -0.0280   0.5093   1.0000
   3.000   0.4639   0.00700   0.00186  -0.0274   0.4626   1.0000
   3.250   0.4885   0.00733   0.00200  -0.0268   0.4092   1.0000
   3.500   0.5125   0.00778   0.00217  -0.0262   0.3416   1.0000
   3.750   0.5362   0.00834   0.00241  -0.0256   0.2623   1.0000
   4.000   0.5590   0.00908   0.00273  -0.0250   0.1698   1.0000
   4.250   0.5811   0.01004   0.00320  -0.0242   0.0746   1.0000
   4.500   0.6059   0.01055   0.00360  -0.0237   0.0551   1.0000
   4.750   0.6313   0.01097   0.00404  -0.0232   0.0494   1.0000
   5.000   0.6569   0.01134   0.00443  -0.0227   0.0454   1.0000
   5.250   0.6810   0.01198   0.00508  -0.0221   0.0411   1.0000
   5.500   0.7060   0.01246   0.00562  -0.0216   0.0390   1.0000
   5.750   0.7313   0.01287   0.00609  -0.0211   0.0363   1.0000
   6.000   0.7559   0.01340   0.00664  -0.0206   0.0338   1.0000
   6.250   0.7759   0.01485   0.00815  -0.0194   0.0305   1.0000
   6.500   0.8021   0.01507   0.00843  -0.0191   0.0289   1.0000
   6.750   0.8269   0.01559   0.00902  -0.0185   0.0268   1.0000
   7.000   0.8510   0.01621   0.00967  -0.0180   0.0250   1.0000
   7.250   0.8694   0.01838   0.01191  -0.0167   0.0227   1.0000
   7.500   0.8952   0.01857   0.01220  -0.0163   0.0217   1.0000
   7.750   0.9195   0.01912   0.01284  -0.0158   0.0202   1.0000
   8.000   0.9431   0.01984   0.01365  -0.0152   0.0190   1.0000
   8.250   0.9661   0.02058   0.01444  -0.0146   0.0180   1.0000
   8.500   0.9826   0.02349   0.01753  -0.0133   0.0169   1.0000
   8.750   1.0047   0.02443   0.01867  -0.0124   0.0164   1.0000
   9.000   1.0254   0.02570   0.02016  -0.0115   0.0156   1.0000
   9.250   1.0454   0.02691   0.02156  -0.0105   0.0147   1.0000
   9.500   1.0653   0.02789   0.02266  -0.0097   0.0140   1.0000
   9.750   1.0837   0.02905   0.02396  -0.0088   0.0135   1.0000
  10.000   1.1001   0.03048   0.02551  -0.0078   0.0131   1.0000
  10.250   1.1065   0.03383   0.02917  -0.0059   0.0127   1.0000
  10.500   1.0957   0.03960   0.03548  -0.0029   0.0125   1.0000
  10.750   1.0940   0.04273   0.03897  -0.0007   0.0124   1.0000
  11.000   1.0818   0.04644   0.04299   0.0019   0.0123   1.0000
  11.250   1.0619   0.05038   0.04719   0.0043   0.0123   1.0000
  11.500   1.0399   0.05514   0.05218   0.0042   0.0123   1.0000
  11.750   1.0167   0.06125   0.05849   0.0012   0.0124   1.0000
  12.500   0.9628   0.08589   0.08359  -0.0184   0.0127   1.0000
  14.250   0.6125   0.15101   0.14885  -0.0310   0.0226   1.0000
  14.500   0.6109   0.15444   0.15228  -0.0325   0.0224   1.0000
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