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MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 117 9.8% (mh117-il)
Reynolds number: 100,000
Max Cl/Cd: 56.43 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh117-il-100000.txt
Download as CSV file: xf-mh117-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 117  9.8%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3200   0.09837   0.09375  -0.0287   1.0000   0.1061
  -9.250  -0.3311   0.09506   0.09050  -0.0313   1.0000   0.1097
  -9.000  -0.3498   0.09175   0.08730  -0.0350   1.0000   0.1107
  -8.750  -0.3291   0.08660   0.08215  -0.0322   1.0000   0.1138
  -8.500  -0.3235   0.08301   0.07859  -0.0318   1.0000   0.1168
  -8.250  -0.3257   0.07934   0.07498  -0.0325   1.0000   0.1196
  -8.000  -0.3493   0.07607   0.07184  -0.0357   1.0000   0.1239
  -7.750  -0.4713   0.06603   0.06148  -0.0520   1.0000   0.0574
  -7.500  -0.4656   0.06326   0.05881  -0.0498   1.0000   0.0559
  -7.250  -0.4699   0.05884   0.05438  -0.0503   1.0000   0.0541
  -7.000  -0.4975   0.04754   0.04227  -0.0541   1.0000   0.0454
  -6.750  -0.4965   0.04332   0.03781  -0.0530   1.0000   0.0450
  -6.500  -0.4928   0.03945   0.03351  -0.0518   1.0000   0.0452
  -6.250  -0.4858   0.03576   0.02932  -0.0506   1.0000   0.0460
  -6.000  -0.4753   0.03285   0.02630  -0.0496   1.0000   0.0485
  -5.750  -0.4609   0.03068   0.02389  -0.0483   1.0000   0.0509
  -5.500  -0.4437   0.02786   0.02053  -0.0471   1.0000   0.0535
  -5.250  -0.4239   0.02558   0.01762  -0.0459   1.0000   0.0582
  -5.000  -0.4054   0.02424   0.01620  -0.0450   1.0000   0.0682
  -4.750  -0.3846   0.02290   0.01456  -0.0440   1.0000   0.0837
  -4.500  -0.3649   0.02184   0.01362  -0.0433   1.0000   0.1041
  -4.250  -0.3446   0.02114   0.01279  -0.0425   1.0000   0.1267
  -4.000  -0.3250   0.02065   0.01233  -0.0418   1.0000   0.1469
  -3.750  -0.2950   0.02003   0.01162  -0.0428   0.9970   0.1693
  -3.500  -0.2539   0.01947   0.01102  -0.0458   0.9900   0.1968
  -3.250  -0.2126   0.01898   0.01064  -0.0489   0.9832   0.2293
  -3.000  -0.1748   0.01849   0.01023  -0.0512   0.9752   0.2679
  -2.750  -0.1322   0.01805   0.01001  -0.0545   0.9689   0.3219
  -2.500  -0.0985   0.01759   0.00981  -0.0560   0.9597   0.3829
  -2.250  -0.0609   0.01715   0.00973  -0.0582   0.9525   0.4665
  -2.000  -0.0273   0.01672   0.00973  -0.0592   0.9442   0.5683
  -1.750   0.0021   0.01633   0.00984  -0.0589   0.9359   0.6933
  -1.500   0.0345   0.01598   0.00992  -0.0580   0.9292   0.8566
  -1.250   0.1143   0.01580   0.00956  -0.0680   0.9272   1.0000
  -1.000   0.1479   0.01592   0.00944  -0.0697   0.9166   1.0000
  -0.750   0.1883   0.01600   0.00934  -0.0724   0.9084   1.0000
  -0.500   0.2321   0.01601   0.00919  -0.0756   0.9010   1.0000
  -0.250   0.2656   0.01613   0.00917  -0.0768   0.8912   1.0000
   0.000   0.3109   0.01604   0.00897  -0.0799   0.8850   1.0000
   0.250   0.3395   0.01618   0.00902  -0.0800   0.8737   1.0000
   0.500   0.3710   0.01626   0.00903  -0.0806   0.8636   1.0000
   0.750   0.4104   0.01614   0.00885  -0.0822   0.8562   1.0000
   1.000   0.4365   0.01628   0.00895  -0.0817   0.8444   1.0000
   1.250   0.4638   0.01640   0.00904  -0.0813   0.8330   1.0000
   1.500   0.4927   0.01646   0.00906  -0.0810   0.8223   1.0000
   1.750   0.5255   0.01635   0.00891  -0.0811   0.8134   1.0000
   2.000   0.5505   0.01647   0.00902  -0.0802   0.8008   1.0000
   2.250   0.5760   0.01658   0.00914  -0.0793   0.7882   1.0000
   2.500   0.6019   0.01665   0.00921  -0.0783   0.7755   1.0000
   2.750   0.6280   0.01670   0.00926  -0.0774   0.7626   1.0000
   3.000   0.6543   0.01673   0.00932  -0.0764   0.7494   1.0000
   3.250   0.6804   0.01674   0.00934  -0.0754   0.7356   1.0000
   3.500   0.7064   0.01675   0.00936  -0.0744   0.7211   1.0000
   3.750   0.7323   0.01674   0.00937  -0.0733   0.7059   1.0000
   4.000   0.7583   0.01671   0.00938  -0.0721   0.6900   1.0000
   4.250   0.7847   0.01665   0.00932  -0.0710   0.6734   1.0000
   4.500   0.8097   0.01664   0.00934  -0.0698   0.6549   1.0000
   4.750   0.8342   0.01664   0.00938  -0.0685   0.6341   1.0000
   5.000   0.8594   0.01660   0.00935  -0.0672   0.6128   1.0000
   5.250   0.8834   0.01659   0.00936  -0.0658   0.5882   1.0000
   5.500   0.9065   0.01662   0.00940  -0.0642   0.5605   1.0000
   5.750   0.9291   0.01669   0.00943  -0.0627   0.5300   1.0000
   6.000   0.9499   0.01688   0.00965  -0.0609   0.4932   1.0000
   6.250   0.9701   0.01719   0.00986  -0.0591   0.4529   1.0000
   6.500   0.9887   0.01768   0.01020  -0.0573   0.4087   1.0000
   6.750   1.0060   0.01840   0.01069  -0.0553   0.3638   1.0000
   7.000   1.0221   0.01932   0.01137  -0.0534   0.3202   1.0000
   7.250   1.0379   0.02037   0.01222  -0.0515   0.2796   1.0000
   7.500   1.0532   0.02153   0.01323  -0.0497   0.2430   1.0000
   7.750   1.0684   0.02276   0.01428  -0.0479   0.2111   1.0000
   8.000   1.0844   0.02410   0.01548  -0.0462   0.1848   1.0000
   8.250   1.1009   0.02551   0.01674  -0.0447   0.1633   1.0000
   8.500   1.1182   0.02688   0.01811  -0.0433   0.1449   1.0000
   8.750   1.1368   0.02839   0.01960  -0.0420   0.1301   1.0000
   9.000   1.1546   0.02989   0.02112  -0.0408   0.1170   1.0000
   9.250   1.1745   0.03170   0.02302  -0.0398   0.1062   1.0000
   9.500   1.1936   0.03353   0.02485  -0.0388   0.0960   1.0000
   9.750   1.2115   0.03528   0.02667  -0.0376   0.0871   1.0000
  10.000   1.2269   0.03752   0.02923  -0.0361   0.0793   1.0000
  10.250   1.2434   0.03999   0.03169  -0.0351   0.0715   1.0000
  10.500   1.2510   0.04183   0.03391  -0.0327   0.0652   1.0000
  10.750   1.2621   0.04481   0.03697  -0.0313   0.0592   1.0000
  11.000   1.2627   0.04708   0.03967  -0.0283   0.0545   1.0000
  11.500   1.2626   0.05309   0.04605  -0.0238   0.0475   1.0000
  11.750   1.2483   0.05611   0.04948  -0.0202   0.0462   1.0000
  12.000   1.2330   0.05950   0.05322  -0.0176   0.0451   1.0000
  12.250   1.2165   0.06302   0.05703  -0.0158   0.0438   1.0000
  12.500   1.1988   0.06718   0.06147  -0.0151   0.0433   1.0000
  12.750   1.1785   0.07194   0.06650  -0.0153   0.0432   1.0000
  13.000   1.1525   0.07805   0.07289  -0.0167   0.0442   1.0000
  13.250   1.1261   0.08468   0.07975  -0.0194   0.0447   1.0000
  13.500   1.1001   0.09211   0.08737  -0.0231   0.0459   1.0000
  13.750   1.0755   0.10010   0.09550  -0.0276   0.0469   1.0000
  14.000   1.0527   0.10859   0.10408  -0.0327   0.0478   1.0000
  14.250   1.0312   0.11776   0.11331  -0.0381   0.0485   1.0000
  14.500   0.9338   0.15811   0.15356  -0.0636   0.0740   1.0000
  14.750   0.9424   0.16238   0.15788  -0.0633   0.0727   1.0000
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