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NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0008-34 (naca000834-il)
Reynolds number: 50,000
Max Cl/Cd: 18.48 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca000834-il-50000-n5.txt
Download as CSV file: xf-naca000834-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008-34                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6438   0.09169   0.08504  -0.0167   1.0000   0.0415
  -8.750  -0.6480   0.08705   0.08042  -0.0185   1.0000   0.0404
  -8.500  -0.6555   0.08264   0.07601  -0.0199   1.0000   0.0392
  -8.250  -0.6630   0.07824   0.07156  -0.0207   1.0000   0.0380
  -8.000  -0.6797   0.07376   0.06657  -0.0219   1.0000   0.0339
  -7.750  -0.6748   0.06936   0.06213  -0.0214   1.0000   0.0334
  -7.500  -0.6726   0.06531   0.05791  -0.0207   1.0000   0.0331
  -7.250  -0.6690   0.06138   0.05374  -0.0196   1.0000   0.0330
  -7.000  -0.6636   0.05756   0.04963  -0.0184   1.0000   0.0328
  -6.750  -0.6560   0.05386   0.04558  -0.0169   1.0000   0.0328
  -6.500  -0.6461   0.05027   0.04153  -0.0152   1.0000   0.0326
  -6.250  -0.6341   0.04680   0.03766  -0.0135   1.0000   0.0323
  -6.000  -0.6199   0.04346   0.03389  -0.0117   1.0000   0.0319
  -5.750  -0.6033   0.04031   0.03028  -0.0098   1.0000   0.0315
  -5.500  -0.5843   0.03736   0.02687  -0.0081   1.0000   0.0314
  -5.250  -0.5627   0.03461   0.02366  -0.0064   1.0000   0.0316
  -5.000  -0.5390   0.03224   0.02080  -0.0049   1.0000   0.0329
  -4.750  -0.5149   0.02986   0.01819  -0.0039   1.0000   0.0359
  -4.500  -0.4893   0.02787   0.01602  -0.0028   1.0000   0.0390
  -4.250  -0.4640   0.02616   0.01399  -0.0013   1.0000   0.0417
  -4.000  -0.4427   0.02454   0.01223   0.0001   1.0000   0.0485
  -3.750  -0.4217   0.02320   0.01064   0.0017   1.0000   0.0573
  -3.500  -0.4014   0.02171   0.00911   0.0030   1.0000   0.0772
  -3.250  -0.3253   0.01948   0.01042   0.0031   1.0000   0.9285
  -3.000  -0.2734   0.01926   0.00949  -0.0018   1.0000   0.9484
  -2.750  -0.2276   0.01896   0.00867  -0.0060   1.0000   0.9670
  -2.500  -0.1790   0.01857   0.00780  -0.0109   1.0000   0.9820
  -2.250  -0.1318   0.01815   0.00704  -0.0158   1.0000   0.9961
  -2.000  -0.1065   0.01781   0.00652  -0.0164   1.0000   1.0000
  -1.750  -0.0911   0.01756   0.00610  -0.0149   1.0000   1.0000
  -1.500  -0.0764   0.01734   0.00579  -0.0132   1.0000   1.0000
  -1.250  -0.0624   0.01716   0.00554  -0.0114   1.0000   1.0000
  -1.000  -0.0491   0.01702   0.00535  -0.0093   1.0000   1.0000
  -0.750  -0.0365   0.01691   0.00520  -0.0071   1.0000   1.0000
  -0.500  -0.0241   0.01683   0.00508  -0.0048   1.0000   1.0000
  -0.250  -0.0120   0.01679   0.00502  -0.0024   1.0000   1.0000
   0.000   0.0000   0.01677   0.00500   0.0000   1.0000   1.0000
   0.250   0.0120   0.01679   0.00502   0.0024   1.0000   1.0000
   0.500   0.0241   0.01683   0.00508   0.0048   1.0000   1.0000
   0.750   0.0365   0.01691   0.00520   0.0071   1.0000   1.0000
   1.000   0.0491   0.01702   0.00534   0.0093   1.0000   1.0000
   1.250   0.0624   0.01716   0.00554   0.0114   1.0000   1.0000
   1.500   0.0764   0.01734   0.00579   0.0132   1.0000   1.0000
   1.750   0.0912   0.01755   0.00610   0.0149   1.0000   1.0000
   2.000   0.1066   0.01781   0.00652   0.0164   1.0000   1.0000
   2.250   0.1317   0.01814   0.00704   0.0158   0.9962   1.0000
   2.500   0.1789   0.01856   0.00779   0.0109   0.9821   1.0000
   2.750   0.2275   0.01895   0.00867   0.0060   0.9671   1.0000
   3.000   0.2734   0.01925   0.00948   0.0018   0.9485   1.0000
   3.250   0.3252   0.01948   0.01041  -0.0031   0.9286   1.0000
   3.500   0.4013   0.02171   0.00911  -0.0030   0.0773   1.0000
   3.750   0.4216   0.02320   0.01064  -0.0016   0.0573   1.0000
   4.000   0.4425   0.02453   0.01223  -0.0001   0.0485   1.0000
   4.250   0.4639   0.02615   0.01398   0.0014   0.0417   1.0000
   4.500   0.4891   0.02786   0.01601   0.0028   0.0390   1.0000
   4.750   0.5147   0.02985   0.01818   0.0039   0.0360   1.0000
   5.000   0.5388   0.03223   0.02079   0.0049   0.0329   1.0000
   5.250   0.5626   0.03460   0.02365   0.0064   0.0316   1.0000
   5.500   0.5842   0.03735   0.02685   0.0081   0.0314   1.0000
   5.750   0.6033   0.04030   0.03027   0.0098   0.0315   1.0000
   6.000   0.6198   0.04346   0.03389   0.0117   0.0319   1.0000
   6.250   0.6341   0.04680   0.03765   0.0135   0.0323   1.0000
   6.500   0.6462   0.05027   0.04153   0.0152   0.0326   1.0000
   6.750   0.6561   0.05387   0.04559   0.0169   0.0328   1.0000
   7.000   0.6637   0.05757   0.04964   0.0183   0.0329   1.0000
   7.250   0.6693   0.06140   0.05376   0.0196   0.0330   1.0000
   7.500   0.6728   0.06533   0.05794   0.0206   0.0332   1.0000
   7.750   0.6751   0.06939   0.06216   0.0213   0.0334   1.0000
   8.250   0.6633   0.07829   0.07161   0.0206   0.0380   1.0000
   8.500   0.6560   0.08270   0.07607   0.0197   0.0393   1.0000
   8.750   0.6487   0.08710   0.08048   0.0184   0.0404   1.0000
   9.000   0.6444   0.09175   0.08510   0.0166   0.0416   1.0000
   9.250   0.6392   0.09875   0.09210   0.0095   0.0484   1.0000
   9.500   0.6374   0.10416   0.09744   0.0063   0.0519   1.0000
   9.750   0.5153   0.09700   0.09053   0.0149   0.0491   1.0000
  10.000   0.5114   0.10175   0.09523   0.0134   0.0518   1.0000
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