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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)
Reynolds number: 50,000
Max Cl/Cd: 30.79 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034a08cli02-il-50000-n5.txt
Download as CSV file: xf-naca001034a08cli02-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4111   0.09209   0.08559  -0.0421   1.0000   0.0419
  -9.250  -0.5166   0.09266   0.08584  -0.0426   1.0000   0.0420
  -9.000  -0.5197   0.08840   0.08164  -0.0438   1.0000   0.0410
  -8.750  -0.5282   0.08422   0.07752  -0.0452   1.0000   0.0402
  -8.500  -0.5411   0.08068   0.07403  -0.0451   1.0000   0.0396
  -8.250  -0.5536   0.07724   0.07061  -0.0442   1.0000   0.0389
  -8.000  -0.5648   0.07377   0.06711  -0.0431   1.0000   0.0382
  -7.750  -0.5745   0.07031   0.06359  -0.0416   1.0000   0.0375
  -7.500  -0.5824   0.06684   0.06001  -0.0398   1.0000   0.0367
  -7.250  -0.5882   0.06334   0.05635  -0.0377   1.0000   0.0359
  -7.000  -0.5914   0.05982   0.05260  -0.0355   1.0000   0.0351
  -6.750  -0.5919   0.05629   0.04878  -0.0332   1.0000   0.0343
  -6.500  -0.5890   0.05283   0.04497  -0.0308   1.0000   0.0335
  -6.250  -0.5830   0.04947   0.04119  -0.0284   1.0000   0.0329
  -6.000  -0.5739   0.04629   0.03755  -0.0260   1.0000   0.0324
  -5.750  -0.5622   0.04342   0.03429  -0.0240   1.0000   0.0327
  -5.500  -0.5486   0.04089   0.03145  -0.0223   1.0000   0.0344
  -5.250  -0.5325   0.03850   0.02866  -0.0206   1.0000   0.0363
  -5.000  -0.5137   0.03613   0.02572  -0.0189   1.0000   0.0378
  -4.750  -0.4924   0.03383   0.02299  -0.0174   1.0000   0.0385
  -4.500  -0.4692   0.03175   0.02054  -0.0160   1.0000   0.0395
  -4.250  -0.4449   0.02995   0.01841  -0.0147   1.0000   0.0410
  -4.000  -0.4212   0.02846   0.01666  -0.0133   1.0000   0.0441
  -3.750  -0.3999   0.02704   0.01517  -0.0122   1.0000   0.0514
  -3.500  -0.3775   0.02593   0.01374  -0.0108   1.0000   0.0565
  -3.250  -0.3551   0.02465   0.01235  -0.0100   1.0000   0.0645
  -3.000  -0.3328   0.02344   0.01114  -0.0093   1.0000   0.0906
  -2.750  -0.2494   0.02077   0.01211  -0.0123   1.0000   0.9596
  -2.500  -0.1863   0.02076   0.01138  -0.0199   1.0000   0.9862
  -2.250  -0.1484   0.02056   0.01076  -0.0233   1.0000   1.0000
  -2.000  -0.1463   0.02031   0.01027  -0.0198   1.0000   1.0000
  -1.750  -0.1417   0.02013   0.00989  -0.0166   1.0000   1.0000
  -1.500  -0.1343   0.02003   0.00958  -0.0138   1.0000   1.0000
  -1.250  -0.1248   0.01999   0.00933  -0.0114   1.0000   1.0000
  -1.000  -0.1131   0.02001   0.00916  -0.0093   1.0000   1.0000
  -0.750  -0.0995   0.02008   0.00904  -0.0075   1.0000   1.0000
  -0.500  -0.0844   0.02021   0.00896  -0.0060   1.0000   1.0000
  -0.250  -0.0642   0.02040   0.00900  -0.0055   0.9986   1.0000
   0.000  -0.0278   0.02076   0.00919  -0.0082   0.9918   1.0000
   0.250   0.0085   0.02113   0.00943  -0.0109   0.9848   1.0000
   0.500   0.0453   0.02151   0.00969  -0.0136   0.9777   1.0000
   0.750   0.0798   0.02184   0.00995  -0.0158   0.9692   1.0000
   1.000   0.1140   0.02218   0.01026  -0.0180   0.9606   1.0000
   1.250   0.1510   0.02255   0.01062  -0.0206   0.9527   1.0000
   1.500   0.1850   0.02286   0.01095  -0.0226   0.9432   1.0000
   1.750   0.2179   0.02316   0.01130  -0.0243   0.9331   1.0000
   2.000   0.2525   0.02346   0.01170  -0.0263   0.9233   1.0000
   2.250   0.2913   0.02375   0.01210  -0.0290   0.9145   1.0000
   2.500   0.3222   0.02399   0.01247  -0.0300   0.9027   1.0000
   2.750   0.3537   0.02422   0.01285  -0.0312   0.8908   1.0000
   3.000   0.3859   0.02443   0.01330  -0.0324   0.8788   1.0000
   3.250   0.4182   0.02461   0.01369  -0.0335   0.8662   1.0000
   3.500   0.4508   0.02474   0.01407  -0.0345   0.8531   1.0000
   3.750   0.4837   0.02481   0.01449  -0.0354   0.8393   1.0000
   4.000   0.5171   0.02481   0.01482  -0.0363   0.8248   1.0000
   4.250   0.5513   0.02470   0.01508  -0.0369   0.8095   1.0000
   4.500   0.5832   0.02454   0.01533  -0.0370   0.7921   1.0000
   4.750   0.6116   0.02439   0.01570  -0.0363   0.7715   1.0000
   5.000   0.6515   0.02116   0.01255  -0.0308   0.6384   1.0000
   5.250   0.6599   0.02246   0.01173  -0.0243   0.2867   1.0000
   5.500   0.6587   0.02562   0.01341  -0.0205   0.1003   1.0000
   5.750   0.6718   0.02755   0.01518  -0.0181   0.0731   1.0000
   6.000   0.6872   0.02913   0.01682  -0.0162   0.0572   1.0000
   6.250   0.7041   0.03099   0.01875  -0.0144   0.0512   1.0000
   6.500   0.7299   0.03272   0.02082  -0.0133   0.0461   1.0000
   6.750   0.7573   0.03515   0.02320  -0.0133   0.0389   1.0000
   7.000   0.7903   0.03751   0.02614  -0.0131   0.0362   1.0000
   7.250   0.8196   0.04047   0.02954  -0.0126   0.0348   1.0000
   7.500   0.8422   0.04362   0.03317  -0.0114   0.0338   1.0000
   7.750   0.8586   0.04669   0.03670  -0.0095   0.0325   1.0000
   8.000   0.8702   0.04965   0.04007  -0.0074   0.0307   1.0000
   8.250   0.8791   0.05261   0.04333  -0.0053   0.0291   1.0000
   8.500   0.8847   0.05588   0.04690  -0.0031   0.0281   1.0000
   8.750   0.8868   0.05939   0.05078  -0.0006   0.0279   1.0000
   9.000   0.8852   0.06293   0.05469   0.0022   0.0280   1.0000
   9.250   0.8788   0.06650   0.05861   0.0050   0.0282   1.0000
   9.500   0.8675   0.07009   0.06251   0.0079   0.0285   1.0000
   9.750   0.8512   0.07354   0.06621   0.0107   0.0288   1.0000
  10.000   0.8331   0.07735   0.07022   0.0124   0.0292   1.0000
  10.250   0.8138   0.08171   0.07474   0.0128   0.0295   1.0000
  10.500   0.7943   0.08676   0.07992   0.0115   0.0299   1.0000
  10.750   0.7756   0.09268   0.08594   0.0086   0.0304   1.0000
  11.000   0.7589   0.09956   0.09286   0.0043   0.0309   1.0000
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