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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)
Reynolds number: 500,000
Max Cl/Cd: 72.99 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034a08cli02-il-500000-n5.txt
Download as CSV file: xf-naca001034a08cli02-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-34 a=0.8 c(li)=0.2                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5163   0.08427   0.08207  -0.0388   1.0000   0.0040
  -9.250  -0.5231   0.07879   0.07663  -0.0422   1.0000   0.0039
  -9.000  -0.5365   0.07274   0.07062  -0.0471   1.0000   0.0038
  -8.750  -0.5611   0.06917   0.06705  -0.0469   1.0000   0.0038
  -8.500  -0.5659   0.06289   0.06065  -0.0515   0.9954   0.0037
  -8.250  -0.5638   0.05654   0.05411  -0.0551   0.9905   0.0037
  -8.000  -0.5563   0.05038   0.04771  -0.0578   0.9872   0.0038
  -7.750  -0.5479   0.04501   0.04207  -0.0585   0.9825   0.0038
  -7.500  -0.5335   0.03997   0.03671  -0.0590   0.9794   0.0041
  -7.250  -0.5139   0.03558   0.03200  -0.0590   0.9770   0.0045
  -7.000  -0.4983   0.03195   0.02804  -0.0578   0.9720   0.0047
  -6.750  -0.4815   0.02775   0.02341  -0.0570   0.9686   0.0046
  -6.500  -0.4621   0.02421   0.01944  -0.0561   0.9654   0.0045
  -6.250  -0.4432   0.02140   0.01624  -0.0545   0.9606   0.0045
  -6.000  -0.4196   0.01903   0.01351  -0.0538   0.9575   0.0045
  -5.750  -0.3939   0.01716   0.01135  -0.0535   0.9552   0.0047
  -5.500  -0.3697   0.01584   0.00979  -0.0528   0.9517   0.0048
  -5.250  -0.3485   0.01403   0.00777  -0.0515   0.9474   0.0053
  -5.000  -0.3243   0.01308   0.00672  -0.0510   0.9440   0.0059
  -4.750  -0.2978   0.01254   0.00612  -0.0509   0.9414   0.0066
  -4.500  -0.2729   0.01218   0.00572  -0.0506   0.9374   0.0079
  -4.250  -0.2487   0.01157   0.00503  -0.0499   0.9331   0.0087
  -4.000  -0.2230   0.01108   0.00444  -0.0496   0.9298   0.0094
  -3.750  -0.1985   0.01040   0.00360  -0.0489   0.9263   0.0115
  -3.500  -0.1732   0.01009   0.00325  -0.0485   0.9217   0.0155
  -3.250  -0.1466   0.00982   0.00291  -0.0484   0.9178   0.0195
  -3.000  -0.1202   0.00943   0.00259  -0.0482   0.9146   0.0476
  -2.750  -0.0992   0.00858   0.00228  -0.0474   0.9090   0.1974
  -2.500  -0.0786   0.00765   0.00202  -0.0466   0.9041   0.3871
  -2.000  -0.0363   0.00646   0.00181  -0.0443   0.8937   0.6615
  -1.750  -0.0113   0.00625   0.00175  -0.0436   0.8888   0.7190
  -1.250   0.0419   0.00609   0.00161  -0.0431   0.8772   0.7635
  -1.000   0.0685   0.00601   0.00156  -0.0429   0.8712   0.7844
  -0.750   0.0952   0.00595   0.00151  -0.0426   0.8643   0.8032
  -0.500   0.1222   0.00589   0.00147  -0.0424   0.8577   0.8197
  -0.250   0.1492   0.00584   0.00145  -0.0422   0.8506   0.8356
   0.000   0.1762   0.00580   0.00144  -0.0421   0.8433   0.8515
   0.250   0.2035   0.00578   0.00144  -0.0419   0.8357   0.8677
   0.500   0.2307   0.00577   0.00146  -0.0418   0.8269   0.8839
   0.750   0.2585   0.00578   0.00149  -0.0417   0.8182   0.8996
   1.000   0.2869   0.00581   0.00152  -0.0418   0.8082   0.9140
   1.250   0.3158   0.00585   0.00158  -0.0420   0.7966   0.9273
   1.500   0.3450   0.00590   0.00163  -0.0424   0.7836   0.9395
   1.750   0.3759   0.00598   0.00168  -0.0430   0.7674   0.9489
   2.000   0.4060   0.00608   0.00174  -0.0436   0.7474   0.9572
   2.250   0.4348   0.00619   0.00183  -0.0439   0.7275   0.9656
   2.500   0.4657   0.00638   0.00191  -0.0446   0.6922   0.9707
   2.750   0.4904   0.00683   0.00202  -0.0441   0.6140   0.9777
   3.000   0.5185   0.00740   0.00224  -0.0446   0.5232   0.9820
   3.250   0.5447   0.00807   0.00252  -0.0448   0.4276   0.9872
   3.500   0.5711   0.00904   0.00289  -0.0454   0.2910   0.9910
   3.750   0.5959   0.01017   0.00337  -0.0457   0.1439   0.9952
   4.000   0.6235   0.01117   0.00389  -0.0465   0.0386   0.9983
   4.250   0.6513   0.01158   0.00427  -0.0469   0.0220   1.0000
   4.500   0.6706   0.01198   0.00471  -0.0453   0.0156   1.0000
   4.750   0.6914   0.01222   0.00500  -0.0441   0.0130   1.0000
   5.000   0.7110   0.01260   0.00541  -0.0426   0.0102   1.0000
   5.250   0.7268   0.01338   0.00631  -0.0402   0.0080   1.0000
   5.500   0.7448   0.01394   0.00695  -0.0383   0.0074   1.0000
   5.750   0.7638   0.01441   0.00748  -0.0367   0.0066   1.0000
   6.000   0.7837   0.01481   0.00791  -0.0354   0.0056   1.0000
   6.250   0.8020   0.01540   0.00861  -0.0337   0.0050   1.0000
   6.500   0.8196   0.01612   0.00939  -0.0319   0.0046   1.0000
   6.750   0.8329   0.01757   0.01097  -0.0293   0.0041   1.0000
   7.000   0.8496   0.01900   0.01255  -0.0273   0.0038   1.0000
   7.250   0.8687   0.02031   0.01404  -0.0257   0.0037   1.0000
   7.500   0.8880   0.02201   0.01595  -0.0242   0.0036   1.0000
   7.750   0.9067   0.02410   0.01831  -0.0226   0.0035   1.0000
   8.000   0.9232   0.02664   0.02118  -0.0207   0.0034   1.0000
   8.250   0.9362   0.02962   0.02453  -0.0182   0.0034   1.0000
   8.500   0.9467   0.03264   0.02790  -0.0155   0.0033   1.0000
   8.750   0.9553   0.03570   0.03129  -0.0126   0.0030   1.0000
   9.000   0.9615   0.03871   0.03460  -0.0097   0.0028   1.0000
   9.250   0.9638   0.04194   0.03811  -0.0065   0.0026   1.0000
   9.500   0.9588   0.04603   0.04250  -0.0026   0.0025   1.0000
   9.750   0.9493   0.04996   0.04670   0.0014   0.0025   1.0000
  10.000   0.9344   0.05350   0.05044   0.0057   0.0025   1.0000
  10.250   0.9173   0.05719   0.05432   0.0092   0.0025   1.0000
  10.500   0.8978   0.06134   0.05865   0.0116   0.0025   1.0000
  10.750   0.8763   0.06614   0.06361   0.0125   0.0025   1.0000
  11.000   0.8540   0.07169   0.06931   0.0115   0.0025   1.0000
  11.250   0.8300   0.07878   0.07653   0.0081   0.0026   1.0000
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