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NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0008-34 (naca000834-il)
Reynolds number: 200,000
Max Cl/Cd: 36.02 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca000834-il-200000-n5.txt
Download as CSV file: xf-naca000834-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5198   0.08601   0.08275  -0.0176   1.0000   0.0167
  -9.250  -0.5259   0.08030   0.07705  -0.0205   1.0000   0.0167
  -9.000  -0.5353   0.07392   0.07067  -0.0248   1.0000   0.0167
  -8.750  -0.5485   0.06857   0.06527  -0.0280   1.0000   0.0167
  -8.500  -0.5642   0.06404   0.06067  -0.0296   1.0000   0.0167
  -8.250  -0.5794   0.06021   0.05677  -0.0293   1.0000   0.0167
  -8.000  -0.5924   0.05652   0.05299  -0.0278   1.0000   0.0167
  -7.750  -0.6000   0.05249   0.04882  -0.0265   1.0000   0.0167
  -7.250  -0.6587   0.05385   0.04966  -0.0196   1.0000   0.0091
  -7.000  -0.6566   0.04988   0.04551  -0.0182   1.0000   0.0086
  -6.750  -0.6511   0.04611   0.04149  -0.0164   1.0000   0.0082
  -6.500  -0.6433   0.04245   0.03756  -0.0142   1.0000   0.0078
  -6.250  -0.6337   0.03891   0.03370  -0.0117   1.0000   0.0073
  -6.000  -0.6224   0.03544   0.02988  -0.0090   1.0000   0.0069
  -5.750  -0.6091   0.03200   0.02604  -0.0062   1.0000   0.0065
  -5.500  -0.5934   0.02845   0.02200  -0.0032   1.0000   0.0060
  -5.250  -0.5750   0.02564   0.01876  -0.0007   1.0000   0.0057
  -5.000  -0.5552   0.02346   0.01620   0.0014   1.0000   0.0055
  -4.750  -0.5346   0.02149   0.01391   0.0031   1.0000   0.0054
  -4.500  -0.5135   0.01952   0.01155   0.0048   1.0000   0.0055
  -4.250  -0.4928   0.01783   0.00968   0.0064   1.0000   0.0056
  -4.000  -0.4731   0.01647   0.00821   0.0080   1.0000   0.0059
  -3.750  -0.4534   0.01542   0.00707   0.0096   1.0000   0.0064
  -3.500  -0.4335   0.01452   0.00606   0.0111   1.0000   0.0074
  -3.250  -0.4126   0.01371   0.00507   0.0125   1.0000   0.0102
  -3.000  -0.3913   0.01319   0.00458   0.0134   1.0000   0.0267
  -2.750  -0.3690   0.01266   0.00400   0.0143   1.0000   0.0403
  -2.500  -0.3438   0.01096   0.00337   0.0136   0.9978   0.2872
  -2.250  -0.3247   0.00902   0.00325   0.0148   0.9953   0.6860
  -2.000  -0.2982   0.00877   0.00342   0.0159   0.9920   0.8150
  -1.750  -0.2662   0.00883   0.00336   0.0155   0.9885   0.8638
  -1.500  -0.2318   0.00902   0.00354   0.0148   0.9863   0.9068
  -1.250  -0.1964   0.00909   0.00352   0.0132   0.9821   0.9217
  -1.000  -0.1580   0.00915   0.00350   0.0108   0.9785   0.9317
  -0.750  -0.1195   0.00919   0.00349   0.0083   0.9749   0.9408
  -0.500  -0.0806   0.00923   0.00347   0.0057   0.9702   0.9482
  -0.250  -0.0396   0.00925   0.00345   0.0027   0.9664   0.9547
   0.000   0.0000   0.00926   0.00346   0.0000   0.9607   0.9607
   0.250   0.0396   0.00925   0.00346  -0.0027   0.9547   0.9664
   0.500   0.0806   0.00923   0.00347  -0.0057   0.9482   0.9702
   0.750   0.1195   0.00919   0.00349  -0.0083   0.9408   0.9749
   1.000   0.1581   0.00915   0.00350  -0.0108   0.9317   0.9786
   1.250   0.1964   0.00909   0.00352  -0.0132   0.9217   0.9821
   1.500   0.2318   0.00902   0.00355  -0.0148   0.9075   0.9863
   1.750   0.2663   0.00883   0.00336  -0.0155   0.8635   0.9885
   2.000   0.2983   0.00877   0.00342  -0.0160   0.8145   0.9920
   2.250   0.3249   0.00902   0.00325  -0.0149   0.6861   0.9953
   2.500   0.3440   0.01094   0.00337  -0.0137   0.2913   0.9978
   2.750   0.3691   0.01266   0.00400  -0.0144   0.0403   1.0000
   3.000   0.3914   0.01319   0.00458  -0.0134   0.0268   1.0000
   3.250   0.4127   0.01373   0.00508  -0.0125   0.0101   1.0000
   3.500   0.4336   0.01453   0.00606  -0.0111   0.0074   1.0000
   3.750   0.4535   0.01543   0.00707  -0.0096   0.0063   1.0000
   4.000   0.4731   0.01648   0.00821  -0.0080   0.0058   1.0000
   4.250   0.4929   0.01784   0.00969  -0.0064   0.0056   1.0000
   4.500   0.5136   0.01952   0.01155  -0.0048   0.0055   1.0000
   4.750   0.5347   0.02149   0.01391  -0.0031   0.0054   1.0000
   5.000   0.5553   0.02346   0.01620  -0.0014   0.0055   1.0000
   5.250   0.5751   0.02565   0.01876   0.0006   0.0057   1.0000
   5.500   0.5934   0.02846   0.02202   0.0031   0.0060   1.0000
   5.750   0.6092   0.03199   0.02603   0.0061   0.0065   1.0000
   6.000   0.6225   0.03544   0.02988   0.0090   0.0069   1.0000
   6.250   0.6337   0.03891   0.03371   0.0117   0.0073   1.0000
   6.500   0.6433   0.04246   0.03756   0.0142   0.0078   1.0000
   6.750   0.6511   0.04611   0.04150   0.0164   0.0082   1.0000
   7.000   0.6566   0.04988   0.04550   0.0182   0.0086   1.0000
   7.250   0.6587   0.05385   0.04966   0.0196   0.0091   1.0000
   7.500   0.6673   0.05933   0.05550   0.0213   0.0128   1.0000
   7.750   0.6673   0.06380   0.06013   0.0217   0.0134   1.0000
   8.000   0.6649   0.06827   0.06473   0.0215   0.0138   1.0000
   8.250   0.6597   0.07283   0.06939   0.0206   0.0141   1.0000
   8.500   0.6501   0.07736   0.07398   0.0191   0.0143   1.0000
   8.750   0.6417   0.08304   0.07969   0.0144   0.0146   1.0000
   9.000   0.6371   0.08904   0.08565   0.0090   0.0150   1.0000
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