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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.67 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001034a08cli02-il-1000000-n5.txt
Download as CSV file: xf-naca001034a08cli02-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5285   0.08041   0.07886  -0.0403   1.0000   0.0014
  -9.250  -0.5383   0.07437   0.07286  -0.0447   1.0000   0.0013
  -9.000  -0.5513   0.06632   0.06477  -0.0542   0.9968   0.0013
  -8.750  -0.5565   0.05926   0.05757  -0.0598   0.9905   0.0013
  -8.500  -0.5571   0.05243   0.05055  -0.0632   0.9853   0.0013
  -8.250  -0.5572   0.04604   0.04391  -0.0640   0.9785   0.0013
  -8.000  -0.5569   0.03940   0.03694  -0.0631   0.9713   0.0012
  -7.750  -0.5592   0.03111   0.02811  -0.0602   0.9639   0.0013
  -7.500  -0.5621   0.02196   0.01816  -0.0553   0.9558   0.0015
  -7.250  -0.5449   0.01890   0.01471  -0.0536   0.9516   0.0017
  -7.000  -0.5231   0.01756   0.01317  -0.0528   0.9471   0.0018
  -6.750  -0.4997   0.01662   0.01208  -0.0522   0.9432   0.0019
  -6.500  -0.4796   0.01444   0.00955  -0.0509   0.9396   0.0021
  -6.250  -0.4587   0.01288   0.00771  -0.0497   0.9353   0.0022
  -6.000  -0.4360   0.01191   0.00659  -0.0489   0.9312   0.0024
  -5.750  -0.4121   0.01121   0.00578  -0.0483   0.9277   0.0026
  -5.500  -0.3866   0.01085   0.00538  -0.0480   0.9240   0.0030
  -5.250  -0.3605   0.01059   0.00510  -0.0479   0.9202   0.0035
  -5.000  -0.3348   0.01023   0.00469  -0.0477   0.9165   0.0041
  -4.750  -0.3098   0.00973   0.00410  -0.0472   0.9131   0.0048
  -4.500  -0.2831   0.00954   0.00388  -0.0472   0.9091   0.0055
  -4.250  -0.2583   0.00901   0.00324  -0.0467   0.9049   0.0067
  -4.000  -0.2322   0.00867   0.00279  -0.0465   0.9012   0.0077
  -3.750  -0.2054   0.00847   0.00258  -0.0465   0.8972   0.0096
  -3.500  -0.1786   0.00826   0.00233  -0.0464   0.8926   0.0114
  -3.250  -0.1514   0.00814   0.00218  -0.0464   0.8884   0.0122
  -3.000  -0.1244   0.00795   0.00194  -0.0464   0.8837   0.0133
  -2.750  -0.0973   0.00779   0.00170  -0.0463   0.8784   0.0151
  -2.500  -0.0702   0.00764   0.00154  -0.0463   0.8734   0.0215
  -2.250  -0.0447   0.00723   0.00135  -0.0460   0.8672   0.0915
  -2.000  -0.0221   0.00649   0.00113  -0.0455   0.8609   0.2564
  -1.750   0.0007   0.00581   0.00099  -0.0450   0.8535   0.4154
  -1.500   0.0248   0.00538   0.00089  -0.0445   0.8464   0.5224
  -1.250   0.0484   0.00497   0.00084  -0.0439   0.8386   0.6334
  -1.000   0.0741   0.00479   0.00082  -0.0435   0.8311   0.6890
  -0.750   0.1012   0.00475   0.00077  -0.0435   0.8230   0.7099
  -0.500   0.1281   0.00469   0.00076  -0.0434   0.8141   0.7348
  -0.250   0.1550   0.00465   0.00075  -0.0433   0.8047   0.7556
   0.000   0.1820   0.00463   0.00074  -0.0432   0.7943   0.7721
   0.250   0.2090   0.00463   0.00074  -0.0431   0.7825   0.7869
   0.500   0.2359   0.00463   0.00074  -0.0430   0.7697   0.8009
   0.750   0.2626   0.00465   0.00076  -0.0428   0.7554   0.8148
   1.000   0.2889   0.00468   0.00079  -0.0426   0.7382   0.8295
   1.250   0.3146   0.00474   0.00083  -0.0422   0.7160   0.8453
   1.500   0.3402   0.00480   0.00090  -0.0418   0.6936   0.8623
   1.750   0.3657   0.00488   0.00097  -0.0414   0.6736   0.8811
   2.000   0.3910   0.00497   0.00106  -0.0409   0.6494   0.9009
   2.250   0.4109   0.00544   0.00121  -0.0393   0.5610   0.9216
   2.500   0.4317   0.00597   0.00141  -0.0381   0.4698   0.9395
   2.750   0.4551   0.00646   0.00162  -0.0374   0.3930   0.9530
   3.000   0.4745   0.00744   0.00198  -0.0363   0.2408   0.9645
   3.250   0.4982   0.00833   0.00235  -0.0361   0.1118   0.9721
   3.500   0.5245   0.00893   0.00266  -0.0363   0.0397   0.9783
   3.750   0.5540   0.00926   0.00290  -0.0369   0.0183   0.9830
   4.000   0.5839   0.00950   0.00313  -0.0377   0.0148   0.9869
   4.250   0.6162   0.00976   0.00343  -0.0389   0.0127   0.9891
   4.500   0.6473   0.01005   0.00378  -0.0399   0.0119   0.9917
   4.750   0.6767   0.01043   0.00428  -0.0406   0.0110   0.9944
   5.000   0.7079   0.01074   0.00463  -0.0417   0.0100   0.9960
   5.250   0.7402   0.01082   0.00467  -0.0431   0.0087   0.9976
   5.500   0.7714   0.01103   0.00483  -0.0444   0.0058   0.9993
   5.750   0.7963   0.01135   0.00515  -0.0441   0.0040   1.0000
   6.000   0.8165   0.01166   0.00547  -0.0428   0.0031   1.0000
   6.250   0.8362   0.01203   0.00584  -0.0413   0.0023   1.0000
   6.500   0.8548   0.01253   0.00642  -0.0396   0.0018   1.0000
   6.750   0.8714   0.01325   0.00726  -0.0374   0.0015   1.0000
   7.000   0.8910   0.01369   0.00779  -0.0360   0.0015   1.0000
   7.250   0.9110   0.01413   0.00829  -0.0347   0.0014   1.0000
   7.500   0.9308   0.01465   0.00888  -0.0334   0.0012   1.0000
   7.750   0.9499   0.01529   0.00961  -0.0320   0.0011   1.0000
   8.000   0.9681   0.01609   0.01052  -0.0304   0.0010   1.0000
   8.250   0.9855   0.01707   0.01164  -0.0287   0.0009   1.0000
   8.500   1.0023   0.01825   0.01299  -0.0269   0.0008   1.0000
   8.750   1.0183   0.01971   0.01465  -0.0250   0.0008   1.0000
   9.000   1.0330   0.02162   0.01682  -0.0229   0.0008   1.0000
   9.250   1.0442   0.02445   0.02003  -0.0203   0.0007   1.0000
   9.500   1.0232   0.03451   0.03109  -0.0123   0.0008   1.0000
   9.750   0.9924   0.04420   0.04141  -0.0042   0.0008   1.0000
  10.000   0.9707   0.04998   0.04751   0.0014   0.0008   1.0000
  10.250   0.9483   0.05423   0.05197   0.0064   0.0009   1.0000
  10.500   0.9260   0.05844   0.05635   0.0099   0.0009   1.0000
  10.750   0.9038   0.06289   0.06095   0.0118   0.0009   1.0000
  11.000   0.8809   0.06796   0.06616   0.0119   0.0009   1.0000
  11.250   0.8588   0.07379   0.07211   0.0100   0.0009   1.0000
  11.500   0.8368   0.08109   0.07952   0.0055   0.0009   1.0000
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