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CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK V AIRFOIL (clarkv-il)
Reynolds number: 50,000
Max Cl/Cd: 36.45 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkv-il-50000-n5.txt
Download as CSV file: xf-clarkv-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK V AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4174   0.10477   0.09755  -0.0425   1.0000   0.0745
  -9.250  -0.4256   0.10145   0.09431  -0.0424   1.0000   0.0745
  -9.000  -0.4359   0.09815   0.09111  -0.0422   1.0000   0.0745
  -8.750  -0.4485   0.09489   0.08795  -0.0417   1.0000   0.0743
  -8.500  -0.4644   0.09171   0.08487  -0.0409   1.0000   0.0740
  -8.250  -0.4833   0.08840   0.08168  -0.0402   1.0000   0.0734
  -8.000  -0.4993   0.08414   0.07749  -0.0410   1.0000   0.0728
  -7.750  -0.5141   0.07944   0.07281  -0.0418   1.0000   0.0722
  -7.500  -0.5273   0.07449   0.06783  -0.0426   1.0000   0.0716
  -7.250  -0.5380   0.06933   0.06255  -0.0433   1.0000   0.0709
  -7.000  -0.5444   0.06423   0.05724  -0.0438   1.0000   0.0705
  -6.750  -0.5449   0.05956   0.05230  -0.0441   1.0000   0.0705
  -6.500  -0.5399   0.05576   0.04821  -0.0440   1.0000   0.0716
  -6.250  -0.5314   0.05222   0.04432  -0.0439   1.0000   0.0736
  -6.000  -0.5199   0.04860   0.04023  -0.0439   1.0000   0.0755
  -5.750  -0.5047   0.04518   0.03629  -0.0439   1.0000   0.0765
  -5.500  -0.4864   0.04217   0.03270  -0.0438   1.0000   0.0775
  -5.250  -0.4658   0.03963   0.02956  -0.0437   1.0000   0.0788
  -5.000  -0.4414   0.03774   0.02744  -0.0442   0.9986   0.0818
  -4.750  -0.4085   0.03630   0.02577  -0.0462   0.9947   0.0857
  -4.500  -0.3754   0.03465   0.02373  -0.0478   0.9906   0.0886
  -4.250  -0.3408   0.03321   0.02184  -0.0494   0.9866   0.0916
  -4.000  -0.3074   0.03202   0.02039  -0.0507   0.9824   0.0953
  -3.750  -0.2748   0.03125   0.01959  -0.0522   0.9776   0.1020
  -3.500  -0.2400   0.03049   0.01861  -0.0538   0.9734   0.1098
  -3.250  -0.2090   0.02979   0.01786  -0.0547   0.9679   0.1175
  -3.000  -0.1738   0.02921   0.01720  -0.0564   0.9634   0.1303
  -2.750  -0.1426   0.02867   0.01661  -0.0575   0.9576   0.1513
  -2.500  -0.1090   0.02803   0.01613  -0.0592   0.9524   0.1865
  -2.250  -0.0729   0.02724   0.01588  -0.0617   0.9483   0.2714
  -2.000  -0.0469   0.02648   0.01578  -0.0619   0.9414   0.4136
  -1.750  -0.0178   0.02584   0.01585  -0.0620   0.9362   0.5757
  -1.500   0.0027   0.02531   0.01605  -0.0590   0.9300   0.7778
  -1.250   0.0510   0.02526   0.01591  -0.0628   0.9231   1.0000
  -1.000   0.0836   0.02551   0.01583  -0.0642   0.9162   1.0000
  -0.750   0.1136   0.02575   0.01578  -0.0652   0.9082   1.0000
  -0.500   0.1448   0.02600   0.01579  -0.0663   0.9009   1.0000
  -0.250   0.1754   0.02625   0.01582  -0.0673   0.8930   1.0000
   0.000   0.2041   0.02651   0.01590  -0.0679   0.8848   1.0000
   0.250   0.2369   0.02674   0.01597  -0.0692   0.8775   1.0000
   0.500   0.2627   0.02701   0.01611  -0.0692   0.8682   1.0000
   0.750   0.2987   0.02720   0.01617  -0.0709   0.8618   1.0000
   1.000   0.3222   0.02749   0.01638  -0.0705   0.8515   1.0000
   1.250   0.3550   0.02768   0.01648  -0.0716   0.8440   1.0000
   1.500   0.3833   0.02789   0.01663  -0.0719   0.8345   1.0000
   1.750   0.4095   0.02813   0.01682  -0.0718   0.8243   1.0000
   2.000   0.4474   0.02810   0.01675  -0.0734   0.8173   1.0000
   2.250   0.4713   0.02830   0.01694  -0.0728   0.8052   1.0000
   2.500   0.4986   0.02841   0.01704  -0.0726   0.7940   1.0000
   2.750   0.5382   0.02812   0.01676  -0.0741   0.7868   1.0000
   3.000   0.5617   0.02827   0.01694  -0.0732   0.7740   1.0000
   3.500   0.6198   0.02822   0.01695  -0.0730   0.7522   1.0000
   3.750   0.6525   0.02803   0.01684  -0.0733   0.7419   1.0000
   4.000   0.6775   0.02809   0.01696  -0.0725   0.7288   1.0000
   4.250   0.7046   0.02806   0.01701  -0.0719   0.7157   1.0000
   4.500   0.7335   0.02793   0.01697  -0.0715   0.7025   1.0000
   4.750   0.7634   0.02772   0.01685  -0.0712   0.6885   1.0000
   5.000   0.7924   0.02750   0.01673  -0.0706   0.6729   1.0000
   5.250   0.8209   0.02727   0.01659  -0.0699   0.6558   1.0000
   5.500   0.8501   0.02701   0.01642  -0.0692   0.6376   1.0000
   5.750   0.8808   0.02673   0.01622  -0.0688   0.6188   1.0000
   6.000   0.9025   0.02687   0.01644  -0.0672   0.5969   1.0000
   6.250   0.9290   0.02685   0.01648  -0.0663   0.5748   1.0000
   6.500   0.9522   0.02702   0.01670  -0.0650   0.5512   1.0000
   6.750   0.9771   0.02715   0.01687  -0.0639   0.5267   1.0000
   7.000   0.9966   0.02754   0.01730  -0.0621   0.5004   1.0000
   7.250   1.0167   0.02795   0.01770  -0.0605   0.4741   1.0000
   7.500   1.0359   0.02842   0.01814  -0.0587   0.4477   1.0000
   7.750   1.0516   0.02905   0.01877  -0.0566   0.4210   1.0000
   8.000   1.0657   0.02979   0.01947  -0.0543   0.3948   1.0000
   8.250   1.0800   0.03059   0.02019  -0.0521   0.3703   1.0000
   8.500   1.0930   0.03151   0.02109  -0.0499   0.3471   1.0000
   8.750   1.1075   0.03245   0.02198  -0.0480   0.3265   1.0000
   9.000   1.1203   0.03351   0.02314  -0.0460   0.3065   1.0000
   9.250   1.1333   0.03461   0.02429  -0.0440   0.2879   1.0000
   9.500   1.1457   0.03575   0.02548  -0.0421   0.2704   1.0000
   9.750   1.1567   0.03695   0.02673  -0.0400   0.2535   1.0000
  10.000   1.1668   0.03822   0.02804  -0.0380   0.2374   1.0000
  10.250   1.1747   0.03957   0.02943  -0.0358   0.2215   1.0000
  10.500   1.1804   0.04105   0.03100  -0.0335   0.2059   1.0000
  10.750   1.1832   0.04269   0.03272  -0.0311   0.1901   1.0000
  11.000   1.1830   0.04452   0.03461  -0.0288   0.1743   1.0000
  11.250   1.1808   0.04655   0.03671  -0.0266   0.1588   1.0000
  11.500   1.1778   0.04880   0.03902  -0.0247   0.1436   1.0000
  11.750   1.1748   0.05125   0.04154  -0.0231   0.1293   1.0000
  12.000   1.1720   0.05388   0.04423  -0.0217   0.1166   1.0000
  12.250   1.1682   0.05674   0.04711  -0.0205   0.1055   1.0000
  12.500   1.1641   0.05982   0.05025  -0.0196   0.0954   1.0000
  12.750   1.1606   0.06308   0.05365  -0.0187   0.0862   1.0000
  13.000   1.1559   0.06649   0.05707  -0.0182   0.0794   1.0000
  13.250   1.1523   0.07000   0.06072  -0.0177   0.0729   1.0000
  13.500   1.1485   0.07350   0.06422  -0.0174   0.0685   1.0000
  13.750   1.1457   0.07729   0.06830  -0.0172   0.0639   1.0000
  14.000   1.1414   0.08108   0.07219  -0.0174   0.0605   1.0000
  14.250   1.1380   0.08477   0.07587  -0.0176   0.0577   1.0000
  14.500   1.1315   0.08949   0.08094  -0.0184   0.0552   1.0000
  14.750   1.1240   0.09442   0.08612  -0.0195   0.0533   1.0000
  15.000   1.1158   0.09955   0.09147  -0.0209   0.0519   1.0000
  15.250   1.1068   0.10495   0.09705  -0.0228   0.0507   1.0000
  15.500   1.0984   0.11036   0.10260  -0.0249   0.0496   1.0000
  15.750   1.0947   0.11479   0.10708  -0.0264   0.0482   1.0000
  16.000   1.0816   0.12164   0.11409  -0.0297   0.0476   1.0000
  16.250   1.0614   0.13067   0.12336  -0.0348   0.0476   1.0000
  16.500   1.0390   0.14104   0.13391  -0.0409   0.0477   1.0000
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