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AUGUST 160 (august160-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AUGUST 160 (august160-il)
Reynolds number: 100,000
Max Cl/Cd: 34.71 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-august160-il-100000-n5.txt
Download as CSV file: xf-august160-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AUGUST 160                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1558   0.09849   0.09237  -0.0442   0.5607   0.0624
  -9.250  -0.1522   0.09532   0.08919  -0.0459   0.5534   0.0641
  -9.000  -0.1635   0.09137   0.08528  -0.0504   0.5497   0.0663
  -8.250  -0.1814   0.07249   0.06639  -0.0603   0.5385   0.0354
  -8.000  -0.1822   0.06950   0.06338  -0.0607   0.5323   0.0347
  -7.750  -0.1903   0.06618   0.05998  -0.0608   0.5280   0.0340
  -7.500  -0.2196   0.05784   0.05135  -0.0625   0.5280   0.0310
  -7.250  -0.2173   0.05493   0.04833  -0.0617   0.5221   0.0307
  -7.000  -0.2139   0.05197   0.04520  -0.0608   0.5162   0.0304
  -6.750  -0.2104   0.04874   0.04171  -0.0595   0.5112   0.0299
  -6.500  -0.2059   0.04538   0.03799  -0.0579   0.5066   0.0295
  -6.250  -0.1981   0.04222   0.03450  -0.0562   0.5008   0.0291
  -6.000  -0.1881   0.03927   0.03114  -0.0543   0.4953   0.0288
  -5.750  -0.1753   0.03665   0.02805  -0.0524   0.4904   0.0287
  -5.500  -0.1595   0.03439   0.02536  -0.0506   0.4850   0.0286
  -5.250  -0.1411   0.03243   0.02301  -0.0491   0.4791   0.0288
  -5.000  -0.1208   0.03079   0.02099  -0.0477   0.4736   0.0291
  -4.750  -0.0991   0.02938   0.01911  -0.0464   0.4690   0.0303
  -4.500  -0.0758   0.02813   0.01755  -0.0453   0.4629   0.0313
  -4.250  -0.0519   0.02728   0.01663  -0.0446   0.4574   0.0324
  -4.000  -0.0271   0.02630   0.01542  -0.0437   0.4527   0.0332
  -3.750  -0.0017   0.02542   0.01433  -0.0429   0.4485   0.0338
  -3.500   0.0238   0.02461   0.01341  -0.0422   0.4434   0.0347
  -3.250   0.0489   0.02390   0.01256  -0.0413   0.4387   0.0356
  -3.000   0.0729   0.02330   0.01193  -0.0405   0.4347   0.0368
  -2.750   0.0970   0.02283   0.01133  -0.0396   0.4312   0.0384
  -2.500   0.1208   0.02243   0.01087  -0.0386   0.4267   0.0404
  -2.250   0.1445   0.02207   0.01052  -0.0377   0.4223   0.0442
  -2.000   0.1684   0.02175   0.01014  -0.0368   0.4185   0.0494
  -1.750   0.1925   0.02141   0.00972  -0.0359   0.4154   0.0575
  -1.500   0.2161   0.02093   0.00934  -0.0349   0.4128   0.0811
  -1.250   0.2390   0.02036   0.00924  -0.0341   0.4095   0.1865
  -1.000   0.3087   0.01861   0.01007  -0.0402   0.4046   0.9037
  -0.750   0.3680   0.01910   0.01025  -0.0452   0.4006   0.9529
  -0.500   0.4272   0.01931   0.01013  -0.0511   0.3972   0.9728
  -0.250   0.5007   0.01941   0.00984  -0.0600   0.3939   0.9954
   0.000   0.5335   0.01959   0.00994  -0.0614   0.3906   1.0000
   0.250   0.5544   0.01980   0.01007  -0.0603   0.3877   1.0000
   0.500   0.5755   0.02002   0.01019  -0.0592   0.3850   1.0000
   0.750   0.5968   0.02024   0.01030  -0.0581   0.3825   1.0000
   1.000   0.6183   0.02046   0.01040  -0.0571   0.3804   1.0000
   1.250   0.6400   0.02070   0.01051  -0.0561   0.3785   1.0000
   1.500   0.6619   0.02097   0.01064  -0.0551   0.3769   1.0000
   1.750   0.6828   0.02133   0.01094  -0.0540   0.3750   1.0000
   2.000   0.7025   0.02174   0.01138  -0.0528   0.3729   1.0000
   2.250   0.7222   0.02217   0.01181  -0.0516   0.3707   1.0000
   2.500   0.7420   0.02259   0.01222  -0.0503   0.3687   1.0000
   2.750   0.7618   0.02301   0.01263  -0.0491   0.3668   1.0000
   3.000   0.7819   0.02343   0.01301  -0.0479   0.3650   1.0000
   3.250   0.8020   0.02384   0.01338  -0.0467   0.3634   1.0000
   3.500   0.8226   0.02422   0.01371  -0.0456   0.3619   1.0000
   3.750   0.8438   0.02458   0.01400  -0.0446   0.3604   1.0000
   4.000   0.8656   0.02494   0.01427  -0.0436   0.3590   1.0000
   4.250   0.8834   0.02553   0.01489  -0.0422   0.3572   1.0000
   4.500   0.8980   0.02628   0.01576  -0.0404   0.3552   1.0000
   4.750   0.9129   0.02705   0.01662  -0.0387   0.3534   1.0000
   5.000   0.9279   0.02781   0.01745  -0.0370   0.3517   1.0000
   5.250   0.9430   0.02857   0.01827  -0.0354   0.3500   1.0000
   5.500   0.9588   0.02927   0.01900  -0.0338   0.3483   1.0000
   5.750   0.9754   0.02991   0.01966  -0.0324   0.3467   1.0000
   6.000   0.9934   0.03045   0.02021  -0.0311   0.3452   1.0000
   6.250   1.0123   0.03098   0.02073  -0.0299   0.3439   1.0000
   6.500   1.0322   0.03151   0.02124  -0.0289   0.3427   1.0000
   6.750   1.0525   0.03209   0.02179  -0.0280   0.3417   1.0000
   7.000   1.0609   0.03330   0.02313  -0.0259   0.3402   1.0000
   7.250   1.0493   0.03551   0.02561  -0.0218   0.3376   1.0000
   7.500   1.0323   0.03801   0.02832  -0.0176   0.3347   1.0000
   7.750   1.0093   0.04073   0.03119  -0.0132   0.3318   1.0000
   8.000   0.9775   0.04408   0.03465  -0.0089   0.3290   1.0000
   8.250   0.9649   0.04699   0.03761  -0.0072   0.3269   1.0000
   8.500   0.9730   0.04854   0.03917  -0.0065   0.3256   1.0000
   8.750   0.9893   0.04947   0.04010  -0.0059   0.3247   1.0000
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