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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 100,000
Max Cl/Cd: 52.56 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2408-il-100000.txt
Download as CSV file: xf-naca2408-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5135   0.10721   0.10220  -0.0076   1.0000   0.0961
  -9.000  -0.5237   0.10425   0.09932  -0.0131   1.0000   0.0997
  -8.750  -0.5419   0.10124   0.09645  -0.0214   1.0000   0.1006
  -8.500  -0.5137   0.09567   0.09081  -0.0139   1.0000   0.1041
  -8.250  -0.5070   0.09235   0.08748  -0.0140   1.0000   0.1084
  -8.000  -0.5151   0.08887   0.08410  -0.0185   1.0000   0.1130
  -7.750  -0.5300   0.08310   0.07837  -0.0323   1.0000   0.1155
  -7.500  -0.5067   0.08095   0.07625  -0.0211   1.0000   0.1215
  -7.250  -0.5148   0.07577   0.07098  -0.0341   1.0000   0.1289
  -7.000  -0.5012   0.07229   0.06763  -0.0282   1.0000   0.1336
  -6.500  -0.4890   0.06430   0.05958  -0.0321   1.0000   0.1481
  -6.250  -0.4842   0.06007   0.05519  -0.0357   1.0000   0.1599
  -6.000  -0.4711   0.04447   0.03810  -0.0437   1.0000   0.0866
  -5.750  -0.4562   0.03954   0.03328  -0.0430   1.0000   0.0827
  -5.500  -0.4397   0.03517   0.02840  -0.0425   1.0000   0.0820
  -5.250  -0.4206   0.03115   0.02381  -0.0417   1.0000   0.0812
  -5.000  -0.3992   0.02798   0.02005  -0.0407   1.0000   0.0827
  -4.750  -0.3764   0.02567   0.01707  -0.0397   1.0000   0.0876
  -4.500  -0.3536   0.02356   0.01484  -0.0390   1.0000   0.0918
  -4.250  -0.3298   0.02244   0.01333  -0.0381   1.0000   0.0999
  -4.000  -0.3054   0.02070   0.01149  -0.0375   1.0000   0.1049
  -3.750  -0.2809   0.01972   0.01034  -0.0367   1.0000   0.1127
  -3.500  -0.2563   0.01860   0.00922  -0.0362   1.0000   0.1212
  -3.250  -0.2308   0.01762   0.00814  -0.0355   1.0000   0.1304
  -3.000  -0.2059   0.01665   0.00727  -0.0350   1.0000   0.1461
  -2.750  -0.1806   0.01568   0.00656  -0.0346   1.0000   0.1806
  -2.500  -0.1548   0.01448   0.00601  -0.0347   1.0000   0.2896
  -2.250  -0.1299   0.01317   0.00575  -0.0345   1.0000   0.4985
  -2.000  -0.1144   0.01207   0.00590  -0.0301   1.0000   0.8381
  -1.750  -0.0790   0.01196   0.00565  -0.0315   1.0000   1.0000
  -1.500  -0.0566   0.01210   0.00555  -0.0310   1.0000   1.0000
  -1.250  -0.0341   0.01227   0.00550  -0.0306   1.0000   1.0000
  -1.000  -0.0117   0.01248   0.00554  -0.0302   1.0000   1.0000
  -0.750   0.0106   0.01272   0.00565  -0.0299   1.0000   1.0000
  -0.500   0.0327   0.01301   0.00581  -0.0296   1.0000   1.0000
  -0.250   0.0545   0.01336   0.00605  -0.0294   1.0000   1.0000
   0.000   0.0852   0.01375   0.00636  -0.0310   0.9968   1.0000
   0.250   0.1380   0.01415   0.00666  -0.0367   0.9865   1.0000
   0.500   0.1893   0.01445   0.00691  -0.0420   0.9749   1.0000
   0.750   0.2379   0.01467   0.00711  -0.0465   0.9616   1.0000
   1.000   0.2865   0.01480   0.00725  -0.0509   0.9484   1.0000
   1.250   0.3380   0.01483   0.00732  -0.0556   0.9363   1.0000
   1.500   0.3850   0.01477   0.00732  -0.0593   0.9224   1.0000
   1.750   0.4285   0.01465   0.00727  -0.0619   0.9078   1.0000
   2.000   0.4643   0.01455   0.00724  -0.0629   0.8897   1.0000
   2.250   0.4993   0.01440   0.00717  -0.0635   0.8716   1.0000
   2.500   0.5328   0.01421   0.00706  -0.0636   0.8535   1.0000
   2.750   0.5618   0.01410   0.00701  -0.0629   0.8329   1.0000
   3.000   0.5895   0.01392   0.00687  -0.0615   0.8098   1.0000
   3.250   0.6142   0.01373   0.00669  -0.0594   0.7806   1.0000
   3.500   0.6373   0.01360   0.00652  -0.0570   0.7463   1.0000
   3.750   0.6604   0.01358   0.00645  -0.0549   0.7102   1.0000
   4.000   0.6837   0.01366   0.00649  -0.0530   0.6743   1.0000
   4.250   0.7066   0.01382   0.00658  -0.0512   0.6351   1.0000
   4.500   0.7298   0.01406   0.00679  -0.0498   0.5972   1.0000
   4.750   0.7518   0.01434   0.00699  -0.0480   0.5503   1.0000
   5.000   0.7731   0.01471   0.00728  -0.0463   0.4959   1.0000
   5.250   0.7906   0.01535   0.00757  -0.0439   0.3945   1.0000
   5.500   0.7946   0.01819   0.00873  -0.0405   0.1565   1.0000
   5.750   0.8114   0.01993   0.01016  -0.0386   0.1195   1.0000
   6.000   0.8309   0.02131   0.01148  -0.0370   0.1070   1.0000
   6.250   0.8517   0.02287   0.01296  -0.0357   0.0990   1.0000
   6.500   0.8747   0.02418   0.01426  -0.0348   0.0900   1.0000
   6.750   0.8998   0.02612   0.01622  -0.0340   0.0848   1.0000
   7.000   0.9243   0.02763   0.01790  -0.0332   0.0780   1.0000
   7.250   0.9496   0.03045   0.02070  -0.0328   0.0730   1.0000
   7.500   0.9728   0.03232   0.02303  -0.0315   0.0686   1.0000
   7.750   0.9949   0.03450   0.02544  -0.0305   0.0640   1.0000
   8.000   1.0156   0.03789   0.02907  -0.0296   0.0618   1.0000
   8.250   1.0301   0.04185   0.03353  -0.0279   0.0599   1.0000
   8.500   1.0421   0.04500   0.03730  -0.0256   0.0585   1.0000
   8.750   1.0512   0.04949   0.04226  -0.0236   0.0590   1.0000
   9.000   1.0586   0.05506   0.04814  -0.0221   0.0602   1.0000
   9.250   1.0424   0.06092   0.05514  -0.0180   0.0680   1.0000
   9.500   0.9576   0.05509   0.04989  -0.0081   0.0687   1.0000
   9.750   0.9629   0.06137   0.05625  -0.0072   0.0749   1.0000
  10.000   0.9130   0.06549   0.06074  -0.0036   0.0766   1.0000
  10.250   0.8763   0.07064   0.06605  -0.0034   0.0771   1.0000
  10.500   0.8398   0.07699   0.07251  -0.0056   0.0772   1.0000
  10.750   0.7732   0.09236   0.08795  -0.0156   0.0904   1.0000
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