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USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 26 AIRFOIL (usa26-il)
Reynolds number: 500,000
Max Cl/Cd: 92.9 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa26-il-500000-n5.txt
Download as CSV file: xf-usa26-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 26 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3791   0.12106   0.11870  -0.0265   1.0000   0.0106
 -11.250  -0.3839   0.11632   0.11397  -0.0273   1.0000   0.0110
 -11.000  -0.3910   0.11130   0.10898  -0.0281   1.0000   0.0114
 -10.750  -0.3883   0.10912   0.10682  -0.0281   1.0000   0.0116
 -10.500  -0.3846   0.10727   0.10499  -0.0278   1.0000   0.0119
 -10.250  -0.3846   0.10464   0.10237  -0.0277   1.0000   0.0120
 -10.000  -0.3853   0.10202   0.09977  -0.0276   1.0000   0.0124
  -9.750  -0.3742   0.09838   0.09614  -0.0309   0.9989   0.0131
  -9.500  -0.3689   0.09298   0.09074  -0.0353   0.9971   0.0138
  -9.250  -0.3764   0.08442   0.08219  -0.0422   0.9944   0.0150
  -9.000  -0.3659   0.08116   0.07893  -0.0455   0.9916   0.0152
  -8.750  -0.3549   0.07781   0.07559  -0.0495   0.9886   0.0155
  -8.500  -0.3418   0.07415   0.07193  -0.0548   0.9856   0.0159
  -8.250  -0.3349   0.07028   0.06805  -0.0592   0.9795   0.0165
  -7.750  -0.3352   0.04780   0.04526  -0.0800   0.9651   0.0196
  -7.500  -0.3094   0.04483   0.04220  -0.0833   0.9630   0.0201
  -7.250  -0.2944   0.04142   0.03867  -0.0843   0.9566   0.0206
  -7.000  -0.2812   0.03249   0.02931  -0.0877   0.9512   0.0222
  -6.750  -0.2808   0.02454   0.02050  -0.0861   0.9429   0.0241
  -6.500  -0.2555   0.02253   0.01811  -0.0863   0.9369   0.0249
  -6.250  -0.2376   0.01989   0.01510  -0.0853   0.9286   0.0256
  -6.000  -0.2105   0.01873   0.01378  -0.0855   0.9209   0.0260
  -5.750  -0.1853   0.01797   0.01289  -0.0852   0.9126   0.0265
  -5.500  -0.1549   0.01731   0.01211  -0.0859   0.9048   0.0271
  -5.250  -0.1274   0.01664   0.01129  -0.0859   0.8934   0.0278
  -5.000  -0.0983   0.01577   0.01025  -0.0862   0.8820   0.0283
  -4.750  -0.0690   0.01488   0.00916  -0.0866   0.8695   0.0287
  -4.500  -0.0398   0.01413   0.00821  -0.0868   0.8537   0.0292
  -4.250  -0.0116   0.01349   0.00738  -0.0868   0.8354   0.0295
  -4.000   0.0152   0.01294   0.00665  -0.0865   0.8157   0.0300
  -3.750   0.0406   0.01249   0.00603  -0.0858   0.7959   0.0303
  -3.500   0.0652   0.01218   0.00558  -0.0850   0.7740   0.0309
  -3.250   0.0889   0.01190   0.00513  -0.0840   0.7486   0.0314
  -3.000   0.1112   0.01165   0.00470  -0.0826   0.7170   0.0317
  -2.750   0.1316   0.01151   0.00434  -0.0809   0.6746   0.0320
  -2.500   0.1510   0.01149   0.00407  -0.0790   0.6251   0.0323
  -2.250   0.1704   0.01144   0.00379  -0.0772   0.5805   0.0326
  -2.000   0.1912   0.01119   0.00337  -0.0756   0.5527   0.0333
  -1.750   0.2136   0.01102   0.00309  -0.0744   0.5326   0.0340
  -1.500   0.2369   0.01091   0.00290  -0.0734   0.5171   0.0347
  -1.250   0.2606   0.01082   0.00274  -0.0725   0.5040   0.0354
  -1.000   0.2847   0.01077   0.00262  -0.0716   0.4922   0.0362
  -0.750   0.3090   0.01071   0.00251  -0.0708   0.4804   0.0371
  -0.500   0.3334   0.01066   0.00241  -0.0701   0.4692   0.0383
  -0.250   0.3579   0.01065   0.00235  -0.0693   0.4585   0.0399
   0.000   0.3822   0.01063   0.00227  -0.0685   0.4480   0.0413
   0.250   0.4070   0.01060   0.00220  -0.0678   0.4382   0.0431
   0.500   0.4312   0.01057   0.00214  -0.0670   0.4290   0.0478
   0.750   0.4558   0.01057   0.00211  -0.0662   0.4196   0.0541
   1.000   0.4801   0.01055   0.00209  -0.0654   0.4112   0.0673
   1.250   0.5022   0.01037   0.00211  -0.0643   0.4028   0.1548
   1.500   0.5256   0.01029   0.00218  -0.0634   0.3954   0.2149
   1.750   0.5493   0.01029   0.00225  -0.0626   0.3879   0.2562
   2.000   0.5735   0.01030   0.00233  -0.0618   0.3812   0.2906
   2.250   0.5967   0.01028   0.00242  -0.0609   0.3740   0.3406
   2.500   0.6186   0.01015   0.00249  -0.0598   0.3675   0.4209
   2.750   0.6916   0.00935   0.00298  -0.0699   0.3553   0.9710
   3.000   0.7289   0.00953   0.00312  -0.0720   0.3471   0.9786
   3.500   0.8044   0.00990   0.00340  -0.0765   0.3353   0.9901
   3.750   0.8497   0.01009   0.00356  -0.0805   0.3296   0.9959
   4.000   0.8910   0.01027   0.00370  -0.0837   0.3243   0.9994
   4.250   0.9177   0.01038   0.00381  -0.0836   0.3204   1.0000
   4.500   0.9392   0.01051   0.00394  -0.0823   0.3157   1.0000
   4.750   0.9599   0.01067   0.00407  -0.0808   0.3109   1.0000
   5.000   0.9812   0.01079   0.00422  -0.0795   0.3055   1.0000
   5.250   1.0019   0.01094   0.00436  -0.0781   0.2984   1.0000
   5.500   1.0223   0.01111   0.00451  -0.0766   0.2916   1.0000
   5.750   1.0427   0.01127   0.00466  -0.0752   0.2829   1.0000
   6.000   1.0628   0.01144   0.00484  -0.0737   0.2744   1.0000
   6.250   1.0819   0.01166   0.00501  -0.0720   0.2591   1.0000
   6.500   1.0991   0.01199   0.00521  -0.0700   0.2322   1.0000
   6.750   1.1099   0.01273   0.00563  -0.0670   0.1784   1.0000
   7.000   1.1220   0.01340   0.00613  -0.0642   0.1489   1.0000
   7.250   1.1362   0.01393   0.00656  -0.0617   0.1289   1.0000
   7.500   1.1492   0.01453   0.00701  -0.0591   0.1049   1.0000
   7.750   1.1515   0.01573   0.00786  -0.0547   0.0492   1.0000
   8.000   1.1553   0.01668   0.00866  -0.0504   0.0180   1.0000
   8.250   1.1677   0.01710   0.00912  -0.0475   0.0151   1.0000
   8.500   1.1813   0.01748   0.00956  -0.0449   0.0141   1.0000
   8.750   1.1944   0.01791   0.01005  -0.0424   0.0132   1.0000
   9.000   1.2060   0.01845   0.01065  -0.0396   0.0119   1.0000
   9.250   1.2168   0.01906   0.01134  -0.0368   0.0111   1.0000
   9.500   1.2283   0.01966   0.01201  -0.0341   0.0107   1.0000
   9.750   1.2407   0.02023   0.01266  -0.0318   0.0103   1.0000
  10.000   1.2521   0.02087   0.01337  -0.0293   0.0099   1.0000
  10.250   1.2628   0.02157   0.01415  -0.0269   0.0093   1.0000
  10.500   1.2722   0.02237   0.01501  -0.0244   0.0090   1.0000
  10.750   1.2819   0.02317   0.01587  -0.0221   0.0084   1.0000
  11.000   1.2877   0.02424   0.01702  -0.0194   0.0081   1.0000
  11.250   1.2888   0.02566   0.01853  -0.0164   0.0078   1.0000
  11.500   1.2924   0.02699   0.01996  -0.0139   0.0077   1.0000
  11.750   1.2989   0.02820   0.02127  -0.0120   0.0075   1.0000
  12.000   1.3025   0.02970   0.02287  -0.0100   0.0073   1.0000
  12.250   1.3047   0.03141   0.02467  -0.0082   0.0071   1.0000
  12.500   1.3057   0.03333   0.02670  -0.0066   0.0070   1.0000
  12.750   1.3047   0.03560   0.02907  -0.0053   0.0068   1.0000
  13.000   1.3049   0.03791   0.03149  -0.0043   0.0067   1.0000
  13.250   1.3029   0.04063   0.03431  -0.0037   0.0065   1.0000
  13.500   1.3016   0.04345   0.03723  -0.0035   0.0064   1.0000
  13.750   1.2964   0.04692   0.04082  -0.0037   0.0063   1.0000
  14.000   1.2928   0.05042   0.04442  -0.0041   0.0062   1.0000
  14.250   1.2897   0.05398   0.04809  -0.0048   0.0060   1.0000
  14.500   1.2824   0.05816   0.05239  -0.0057   0.0059   1.0000
  14.750   1.2768   0.06218   0.05650  -0.0066   0.0059   1.0000
  15.000   1.2709   0.06625   0.06065  -0.0076   0.0058   1.0000
  15.250   1.2600   0.07099   0.06549  -0.0087   0.0056   1.0000
  15.500   1.2518   0.07541   0.07001  -0.0098   0.0056   1.0000
  15.750   1.2401   0.08033   0.07501  -0.0111   0.0054   1.0000
  16.000   1.2334   0.08460   0.07936  -0.0122   0.0055   1.0000
  16.250   1.2266   0.08889   0.08373  -0.0132   0.0055   1.0000
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