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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 100,000
Max Cl/Cd: 34.06 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh83-il-100000.txt
Download as CSV file: xf-mh83-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2550   0.11849   0.11442  -0.0068   1.0000   0.0805
  -9.500  -0.2600   0.11720   0.11323  -0.0120   1.0000   0.0828
  -9.250  -0.2693   0.11623   0.11240  -0.0189   1.0000   0.0834
  -9.000  -0.2284   0.10865   0.10486  -0.0146   1.0000   0.0864
  -8.750  -0.2127   0.10544   0.10174  -0.0170   1.0000   0.0898
  -8.500  -0.2003   0.10257   0.09891  -0.0245   0.9526   0.0943
  -8.250  -0.2056   0.10059   0.09690  -0.0357   0.9083   0.0961
  -8.000  -0.1758   0.09534   0.09152  -0.0300   0.8815   0.0983
  -7.750  -0.1662   0.09293   0.08903  -0.0285   0.8562   0.1008
  -7.500  -0.1616   0.09071   0.08675  -0.0284   0.8343   0.1041
  -7.250  -0.1699   0.08930   0.08533  -0.0316   0.8153   0.1084
  -7.000  -0.1904   0.08801   0.08406  -0.0414   0.7992   0.1099
  -6.750  -0.1646   0.08347   0.07945  -0.0324   0.7838   0.1120
  -6.500  -0.1508   0.08085   0.07677  -0.0306   0.7689   0.1152
  -6.250  -0.1461   0.07863   0.07448  -0.0314   0.7560   0.1192
  -6.000  -0.1508   0.07499   0.07082  -0.0454   0.7437   0.1255
  -5.750  -0.1350   0.07225   0.06806  -0.0397   0.7303   0.1275
  -5.500  -0.1210   0.06988   0.06562  -0.0383   0.7187   0.1315
  -5.250  -0.1102   0.06551   0.06112  -0.0503   0.7076   0.1418
  -5.000  -0.0948   0.06313   0.05875  -0.0466   0.6953   0.1445
  -4.750  -0.0784   0.06067   0.05616  -0.0472   0.6853   0.1515
  -4.500  -0.0604   0.05719   0.05262  -0.0511   0.6732   0.1615
  -4.250  -0.0344   0.04111   0.03675  -0.0472   0.6442   0.1767
  -4.000   0.0066   0.03722   0.03100  -0.0716   0.6587   0.0859
  -3.750   0.0349   0.03286   0.02593  -0.0726   0.6502   0.0768
  -3.500   0.0666   0.02949   0.02157  -0.0734   0.6387   0.0720
  -3.250   0.0945   0.02753   0.01915  -0.0730   0.6294   0.0719
  -3.000   0.1233   0.02586   0.01712  -0.0729   0.6179   0.0730
  -2.750   0.1506   0.02481   0.01603  -0.0726   0.6072   0.0775
  -2.500   0.1791   0.02385   0.01471  -0.0720   0.5978   0.0825
  -2.250   0.2073   0.02278   0.01365  -0.0717   0.5867   0.0880
  -2.000   0.2349   0.02192   0.01263  -0.0709   0.5787   0.0992
  -1.750   0.2632   0.02119   0.01200  -0.0707   0.5673   0.1233
  -1.500   0.2903   0.02020   0.01130  -0.0702   0.5595   0.1957
  -1.250   0.3176   0.01981   0.01128  -0.0702   0.5492   0.2876
  -1.000   0.3439   0.01942   0.01114  -0.0696   0.5417   0.3845
  -0.750   0.3691   0.01903   0.01119  -0.0688   0.5319   0.4958
  -0.500   0.3914   0.01848   0.01107  -0.0667   0.5255   0.6536
  -0.250   0.4212   0.01780   0.01098  -0.0656   0.5154   1.0000
   0.000   0.4508   0.01804   0.01075  -0.0656   0.5092   1.0000
   0.250   0.4796   0.01850   0.01105  -0.0660   0.5001   1.0000
   0.500   0.5083   0.01875   0.01099  -0.0658   0.4936   1.0000
   0.750   0.5364   0.01922   0.01129  -0.0660   0.4858   1.0000
   1.000   0.5646   0.01955   0.01141  -0.0659   0.4788   1.0000
   1.250   0.5928   0.01992   0.01152  -0.0657   0.4734   1.0000
   1.500   0.6202   0.02051   0.01209  -0.0659   0.4659   1.0000
   1.750   0.6482   0.02086   0.01225  -0.0658   0.4604   1.0000
   2.000   0.6757   0.02137   0.01262  -0.0657   0.4549   1.0000
   2.250   0.7026   0.02197   0.01320  -0.0658   0.4480   1.0000
   2.500   0.7304   0.02232   0.01337  -0.0656   0.4431   1.0000
   2.750   0.7575   0.02294   0.01390  -0.0656   0.4384   1.0000
   3.000   0.7833   0.02376   0.01477  -0.0657   0.4324   1.0000
   3.250   0.8104   0.02423   0.01514  -0.0656   0.4276   1.0000
   3.500   0.8385   0.02462   0.01533  -0.0653   0.4240   1.0000
   3.750   0.8620   0.02573   0.01660  -0.0655   0.4178   1.0000
   4.000   0.8878   0.02644   0.01730  -0.0655   0.4130   1.0000
   4.250   0.9150   0.02695   0.01770  -0.0653   0.4094   1.0000
   4.500   0.9415   0.02765   0.01831  -0.0652   0.4060   1.0000
   4.750   0.9617   0.02916   0.02006  -0.0653   0.4001   1.0000
   5.000   0.9868   0.02988   0.02077  -0.0652   0.3957   1.0000
   5.250   1.0140   0.03032   0.02112  -0.0649   0.3924   1.0000
   5.500   1.0391   0.03124   0.02198  -0.0648   0.3893   1.0000
   5.750   1.0521   0.03364   0.02474  -0.0649   0.3836   1.0000
   6.000   1.0742   0.03470   0.02584  -0.0647   0.3794   1.0000
   6.250   1.1020   0.03502   0.02606  -0.0644   0.3764   1.0000
   6.500   1.1312   0.03535   0.02625  -0.0641   0.3738   1.0000
   6.750   1.1224   0.04026   0.03171  -0.0642   0.3675   1.0000
   7.000   1.1321   0.04268   0.03428  -0.0640   0.3631   1.0000
   7.250   1.1620   0.04268   0.03420  -0.0635   0.3604   1.0000
   7.500   1.1977   0.04216   0.03355  -0.0631   0.3582   1.0000
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