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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 50,000
Max Cl/Cd: 32.33 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1408-il-50000.txt
Download as CSV file: xf-naca1408-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4807   0.12855   0.12170   0.0043   1.0000   0.2213
 -10.500  -0.4586   0.12283   0.11595   0.0052   1.0000   0.2309
 -10.250  -0.4821   0.12198   0.11518   0.0035   1.0000   0.2361
 -10.000  -0.4657   0.11711   0.11030   0.0044   1.0000   0.2494
  -9.750  -0.4539   0.11270   0.10589   0.0049   1.0000   0.2607
  -9.500  -0.4536   0.10908   0.10228   0.0048   1.0000   0.2695
  -9.250  -0.4698   0.10717   0.10046   0.0040   1.0000   0.2795
  -9.000  -0.4507   0.10210   0.09534   0.0049   1.0000   0.2912
  -8.750  -0.4457   0.09806   0.09132   0.0051   1.0000   0.3009
  -8.500  -0.4481   0.09453   0.08784   0.0051   1.0000   0.3125
  -8.250  -0.4434   0.09079   0.08412   0.0058   1.0000   0.3278
  -8.000  -0.4373   0.08705   0.08040   0.0066   1.0000   0.3448
  -7.750  -0.4339   0.08333   0.07671   0.0073   1.0000   0.3602
  -7.500  -0.5681   0.09125   0.08444   0.0163   1.0000   0.3540
  -7.250  -0.5465   0.08706   0.08021   0.0184   1.0000   0.3768
  -7.000  -0.5518   0.08439   0.07764   0.0194   1.0000   0.3985
  -6.750  -0.5352   0.08041   0.07363   0.0207   1.0000   0.4175
  -6.500  -0.5765   0.06759   0.06084  -0.0090   1.0000   0.2610
  -6.250  -0.5733   0.04968   0.04162  -0.0277   1.0000   0.1457
  -6.000  -0.5578   0.04519   0.03671  -0.0280   1.0000   0.1443
  -5.750  -0.5402   0.04110   0.03211  -0.0279   1.0000   0.1440
  -5.500  -0.5201   0.03725   0.02769  -0.0274   1.0000   0.1428
  -5.250  -0.4982   0.03417   0.02404  -0.0267   1.0000   0.1456
  -5.000  -0.4756   0.03156   0.02099  -0.0259   1.0000   0.1525
  -4.750  -0.4512   0.02926   0.01843  -0.0250   1.0000   0.1585
  -4.500  -0.4262   0.02715   0.01600  -0.0241   1.0000   0.1675
  -4.250  -0.4017   0.02546   0.01422  -0.0232   1.0000   0.1830
  -4.000  -0.3758   0.02371   0.01240  -0.0222   1.0000   0.2006
  -3.750  -0.3502   0.02210   0.01084  -0.0212   1.0000   0.2363
  -3.500  -0.3262   0.02006   0.00942  -0.0200   1.0000   0.3195
  -3.250  -0.3137   0.01759   0.00857  -0.0162   1.0000   0.5378
  -3.000  -0.3058   0.01655   0.00876  -0.0075   1.0000   0.7952
  -2.750  -0.1494   0.01674   0.00780  -0.0280   1.0000   1.0000
  -2.500  -0.1402   0.01627   0.00710  -0.0263   1.0000   1.0000
  -2.250  -0.1289   0.01597   0.00660  -0.0244   1.0000   1.0000
  -2.000  -0.1161   0.01578   0.00621  -0.0224   1.0000   1.0000
  -1.750  -0.1020   0.01565   0.00590  -0.0205   1.0000   1.0000
  -1.500  -0.0869   0.01558   0.00566  -0.0186   1.0000   1.0000
  -1.250  -0.0705   0.01555   0.00545  -0.0170   1.0000   1.0000
  -1.000  -0.0532   0.01556   0.00532  -0.0155   1.0000   1.0000
  -0.750  -0.0351   0.01560   0.00524  -0.0141   1.0000   1.0000
  -0.500  -0.0164   0.01568   0.00522  -0.0129   1.0000   1.0000
  -0.250   0.0028   0.01579   0.00523  -0.0117   1.0000   1.0000
   0.000   0.0223   0.01594   0.00531  -0.0108   1.0000   1.0000
   0.250   0.0420   0.01612   0.00544  -0.0099   1.0000   1.0000
   0.500   0.0618   0.01635   0.00563  -0.0091   1.0000   1.0000
   0.750   0.0815   0.01662   0.00588  -0.0084   1.0000   1.0000
   1.000   0.1012   0.01695   0.00620  -0.0078   1.0000   1.0000
   1.250   0.1206   0.01733   0.00660  -0.0073   1.0000   1.0000
   1.500   0.1396   0.01779   0.00708  -0.0070   1.0000   1.0000
   1.750   0.1583   0.01833   0.00766  -0.0068   1.0000   1.0000
   2.000   0.1765   0.01896   0.00836  -0.0068   1.0000   1.0000
   2.250   0.1941   0.01969   0.00915  -0.0069   1.0000   1.0000
   2.500   0.2112   0.02054   0.01008  -0.0072   1.0000   1.0000
   2.750   0.2599   0.02168   0.01142  -0.0136   0.9855   1.0000
   3.000   0.3377   0.02271   0.01278  -0.0245   0.9537   1.0000
   3.250   0.4088   0.02324   0.01372  -0.0329   0.9176   1.0000
   3.500   0.4836   0.02310   0.01406  -0.0403   0.8786   1.0000
   3.750   0.5427   0.02236   0.01379  -0.0427   0.8355   1.0000
   4.000   0.5831   0.02131   0.01303  -0.0403   0.7852   1.0000
   4.250   0.6080   0.02029   0.01209  -0.0347   0.7249   1.0000
   4.500   0.6237   0.01967   0.01132  -0.0281   0.6457   1.0000
   4.750   0.6369   0.01970   0.01103  -0.0224   0.5406   1.0000
   5.000   0.6411   0.02149   0.01137  -0.0162   0.3286   1.0000
   5.250   0.6581   0.02429   0.01310  -0.0140   0.2186   1.0000
   5.500   0.6846   0.02650   0.01497  -0.0130   0.1862   1.0000
   5.750   0.7112   0.02842   0.01696  -0.0122   0.1651   1.0000
   6.000   0.7383   0.03063   0.01931  -0.0115   0.1525   1.0000
   6.250   0.7650   0.03321   0.02191  -0.0109   0.1440   1.0000
   6.500   0.7884   0.03552   0.02469  -0.0098   0.1350   1.0000
   6.750   0.8122   0.03876   0.02805  -0.0091   0.1303   1.0000
   7.000   0.8314   0.04210   0.03211  -0.0077   0.1282   1.0000
   7.250   0.8469   0.04564   0.03628  -0.0064   0.1248   1.0000
   7.500   0.8598   0.04977   0.04099  -0.0053   0.1239   1.0000
   7.750   0.8688   0.05471   0.04646  -0.0044   0.1265   1.0000
   8.000   0.8782   0.05981   0.05187  -0.0038   0.1292   1.0000
   8.250   0.8649   0.06693   0.05974  -0.0045   0.1385   1.0000
   8.500   0.8698   0.07269   0.06563  -0.0048   0.1434   1.0000
   8.750   0.8202   0.08401   0.07732  -0.0129   0.1668   1.0000
   9.000   0.7159   0.10972   0.10273  -0.0492   0.3485   1.0000
   9.250   0.7223   0.11443   0.10743  -0.0495   0.3427   1.0000
   9.500   0.7361   0.11905   0.11210  -0.0488   0.3296   1.0000
   9.750   0.7463   0.12339   0.11647  -0.0481   0.3157   1.0000
  10.000   0.5712   0.11706   0.11029  -0.0328   0.3195   1.0000
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