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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 100,000
Max Cl/Cd: 44.19 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1408-il-100000.txt
Download as CSV file: xf-naca1408-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5966   0.10482   0.09980   0.0042   1.0000   0.1145
  -9.000  -0.6051   0.10091   0.09595  -0.0003   1.0000   0.1197
  -8.750  -0.6405   0.09570   0.09089  -0.0145   1.0000   0.1214
  -8.500  -0.6004   0.09242   0.08754  -0.0024   1.0000   0.1260
  -8.250  -0.6005   0.08866   0.08382  -0.0045   1.0000   0.1314
  -8.000  -0.6317   0.08155   0.07671  -0.0196   1.0000   0.1362
  -7.750  -0.6030   0.07979   0.07503  -0.0104   1.0000   0.1417
  -7.500  -0.6227   0.07311   0.06817  -0.0227   1.0000   0.1504
  -7.250  -0.5974   0.07123   0.06645  -0.0159   1.0000   0.1586
  -7.000  -0.5950   0.06654   0.06171  -0.0187   1.0000   0.1682
  -6.750  -0.5910   0.06221   0.05726  -0.0214   1.0000   0.1808
  -6.500  -0.5903   0.04122   0.03407  -0.0301   1.0000   0.0796
  -6.250  -0.5738   0.03652   0.02918  -0.0295   1.0000   0.0774
  -6.000  -0.5555   0.03279   0.02497  -0.0284   1.0000   0.0765
  -5.750  -0.5351   0.03024   0.02178  -0.0271   1.0000   0.0791
  -5.500  -0.5133   0.02769   0.01870  -0.0258   1.0000   0.0804
  -5.250  -0.4911   0.02498   0.01584  -0.0250   1.0000   0.0832
  -5.000  -0.4678   0.02359   0.01429  -0.0241   1.0000   0.0894
  -4.750  -0.4431   0.02214   0.01245  -0.0229   1.0000   0.0934
  -4.500  -0.4194   0.02043   0.01082  -0.0222   1.0000   0.0997
  -4.250  -0.3948   0.01940   0.00960  -0.0212   1.0000   0.1079
  -4.000  -0.3712   0.01807   0.00841  -0.0203   1.0000   0.1166
  -3.750  -0.3479   0.01703   0.00745  -0.0194   1.0000   0.1313
  -3.500  -0.3252   0.01590   0.00653  -0.0183   1.0000   0.1582
  -3.250  -0.3044   0.01415   0.00558  -0.0173   1.0000   0.2691
  -3.000  -0.2854   0.01274   0.00524  -0.0158   1.0000   0.4750
  -2.750  -0.2669   0.01192   0.00515  -0.0132   1.0000   0.6514
  -2.500  -0.2492   0.01150   0.00529  -0.0091   1.0000   0.8193
  -2.250  -0.1737   0.01167   0.00536  -0.0160   1.0000   0.9740
  -2.000  -0.1124   0.01157   0.00493  -0.0232   1.0000   1.0000
  -1.750  -0.1019   0.01143   0.00467  -0.0206   1.0000   1.0000
  -1.500  -0.0893   0.01137   0.00448  -0.0183   1.0000   1.0000
  -1.250  -0.0746   0.01137   0.00435  -0.0163   1.0000   1.0000
  -1.000  -0.0578   0.01140   0.00427  -0.0146   1.0000   1.0000
  -0.750  -0.0395   0.01148   0.00425  -0.0133   1.0000   1.0000
  -0.500  -0.0203   0.01159   0.00428  -0.0121   1.0000   1.0000
  -0.250  -0.0005   0.01173   0.00435  -0.0112   1.0000   1.0000
   0.000   0.0198   0.01192   0.00448  -0.0104   1.0000   1.0000
   0.250   0.0402   0.01215   0.00467  -0.0097   1.0000   1.0000
   0.500   0.0607   0.01243   0.00493  -0.0092   1.0000   1.0000
   0.750   0.0810   0.01277   0.00526  -0.0088   1.0000   1.0000
   1.000   0.1140   0.01317   0.00567  -0.0110   0.9956   1.0000
   1.250   0.1723   0.01351   0.00606  -0.0177   0.9814   1.0000
   1.500   0.2284   0.01370   0.00634  -0.0238   0.9645   1.0000
   1.750   0.2853   0.01375   0.00651  -0.0296   0.9470   1.0000
   2.000   0.3427   0.01363   0.00656  -0.0352   0.9295   1.0000
   2.250   0.3899   0.01343   0.00650  -0.0383   0.9075   1.0000
   2.500   0.4320   0.01313   0.00633  -0.0398   0.8833   1.0000
   2.750   0.4626   0.01293   0.00623  -0.0389   0.8531   1.0000
   3.000   0.4881   0.01280   0.00614  -0.0370   0.8179   1.0000
   3.250   0.5118   0.01270   0.00603  -0.0346   0.7786   1.0000
   3.500   0.5331   0.01268   0.00592  -0.0318   0.7279   1.0000
   3.750   0.5535   0.01279   0.00585  -0.0289   0.6664   1.0000
   4.000   0.5745   0.01306   0.00593  -0.0267   0.6037   1.0000
   4.250   0.5953   0.01347   0.00610  -0.0246   0.5332   1.0000
   4.500   0.6148   0.01406   0.00636  -0.0225   0.4361   1.0000
   4.750   0.6251   0.01622   0.00711  -0.0197   0.1998   1.0000
   5.000   0.6420   0.01820   0.00845  -0.0179   0.1328   1.0000
   5.250   0.6631   0.01955   0.00966  -0.0167   0.1145   1.0000
   5.500   0.6858   0.02096   0.01093  -0.0156   0.1041   1.0000
   5.750   0.7104   0.02220   0.01224  -0.0148   0.0948   1.0000
   6.000   0.7353   0.02410   0.01406  -0.0141   0.0887   1.0000
   6.250   0.7610   0.02557   0.01578  -0.0133   0.0830   1.0000
   6.500   0.7855   0.02768   0.01784  -0.0129   0.0772   1.0000
   6.750   0.8099   0.03012   0.02067  -0.0118   0.0749   1.0000
   7.000   0.8322   0.03222   0.02329  -0.0106   0.0712   1.0000
   7.250   0.8532   0.03475   0.02621  -0.0094   0.0685   1.0000
   7.500   0.8712   0.03831   0.03032  -0.0078   0.0686   1.0000
   7.750   0.8850   0.04257   0.03520  -0.0061   0.0698   1.0000
   8.000   0.8956   0.04684   0.03999  -0.0045   0.0701   1.0000
   8.250   0.9014   0.05188   0.04552  -0.0031   0.0719   1.0000
   8.500   0.9169   0.05728   0.05100  -0.0024   0.0775   1.0000
   9.250   0.8358   0.09320   0.08854  -0.0131   0.1582   1.0000
   9.500   0.7911   0.10153   0.09677  -0.0248   0.1572   1.0000
   9.750   0.7714   0.10709   0.10225  -0.0307   0.1501   1.0000
  10.000   0.7899   0.11037   0.10557  -0.0269   0.1437   1.0000
  10.250   0.7650   0.11622   0.11131  -0.0343   0.1381   1.0000
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