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MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 78 14.47% (mh78-il)
Reynolds number: 50,000
Max Cl/Cd: 9.88 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh78-il-50000.txt
Download as CSV file: xf-mh78-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 78  14.47%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4864   0.12459   0.11902   0.0369   1.0000   0.2647
  -9.250  -0.4414   0.11762   0.11209   0.0389   1.0000   0.2737
  -9.000  -0.4806   0.11786   0.11249   0.0351   1.0000   0.2842
  -8.750  -0.4285   0.11061   0.10528   0.0372   1.0000   0.2929
  -8.500  -0.4457   0.10843   0.10324   0.0351   1.0000   0.3052
  -8.250  -0.4154   0.10349   0.09837   0.0354   1.0000   0.3128
  -8.000  -0.4247   0.10063   0.09566   0.0338   1.0000   0.3259
  -7.750  -0.4022   0.09630   0.09143   0.0334   1.0000   0.3329
  -7.500  -0.4068   0.09314   0.08844   0.0319   1.0000   0.3463
  -7.250  -0.5744   0.06691   0.06129  -0.0013   1.0000   0.1418
  -7.000  -0.5503   0.06232   0.05686  -0.0024   1.0000   0.1376
  -6.750  -0.5594   0.05578   0.04969  -0.0037   1.0000   0.1258
  -6.500  -0.5425   0.05180   0.04569  -0.0054   1.0000   0.1232
  -6.250  -0.5501   0.04985   0.04368  -0.0041   0.9994   0.1214
  -6.000  -0.5004   0.04330   0.03615  -0.0114   0.9570   0.1163
  -5.750  -0.4521   0.03960   0.03192  -0.0157   0.9168   0.1179
  -5.500  -0.4240   0.03763   0.02953  -0.0153   0.8800   0.1221
  -5.250  -0.4051   0.03609   0.02745  -0.0128   0.8483   0.1256
  -5.000  -0.3857   0.03454   0.02565  -0.0101   0.8216   0.1295
  -4.750  -0.3644   0.03344   0.02442  -0.0080   0.7944   0.1374
  -4.500  -0.3420   0.03224   0.02310  -0.0060   0.7708   0.1477
  -4.250  -0.3182   0.03110   0.02191  -0.0040   0.7489   0.1636
  -4.000  -0.2930   0.03003   0.02078  -0.0022   0.7284   0.1902
  -3.750  -0.2666   0.02855   0.01967  -0.0007   0.7091   0.2461
  -3.500  -0.2508   0.02622   0.01862   0.0021   0.6923   0.3943
  -3.250  -0.2379   0.02473   0.01881   0.0079   0.6765   0.6342
  -3.000  -0.1685   0.02775   0.02189   0.0117   0.6523   0.8333
  -2.750  -0.0482   0.03031   0.02356   0.0034   0.6215   0.9199
  -2.500   0.0602   0.02997   0.02255  -0.0097   0.5940   0.9808
  -2.250   0.1137   0.02928   0.02151  -0.0161   0.5768   1.0000
  -2.000   0.1276   0.02918   0.02112  -0.0151   0.5674   1.0000
  -1.750   0.1491   0.02946   0.02129  -0.0160   0.5547   1.0000
  -1.500   0.1646   0.02954   0.02109  -0.0145   0.5463   1.0000
  -1.250   0.1891   0.03017   0.02168  -0.0160   0.5342   1.0000
  -1.000   0.2064   0.03039   0.02163  -0.0144   0.5265   1.0000
  -0.750   0.2315   0.03130   0.02254  -0.0160   0.5152   1.0000
  -0.500   0.2504   0.03166   0.02270  -0.0148   0.5076   1.0000
  -0.250   0.2742   0.03280   0.02381  -0.0160   0.4987   1.0000
   0.000   0.2958   0.03370   0.02464  -0.0162   0.4906   1.0000
   0.250   0.3130   0.03407   0.02476  -0.0140   0.4851   1.0000
   0.500   0.3378   0.03619   0.02703  -0.0172   0.4753   1.0000
   0.750   0.3570   0.03720   0.02795  -0.0166   0.4691   1.0000
   1.000   0.3746   0.03792   0.02848  -0.0148   0.4644   1.0000
   1.250   0.3937   0.04123   0.03201  -0.0190   0.4564   1.0000
   1.500   0.4097   0.04289   0.03363  -0.0189   0.4506   1.0000
   1.750   0.4265   0.04369   0.03429  -0.0169   0.4465   1.0000
   2.000   0.4369   0.04698   0.03765  -0.0188   0.4427   1.0000
   2.250   0.4359   0.05155   0.04235  -0.0219   0.4397   1.0000
   2.500   0.4304   0.05559   0.04643  -0.0234   0.4389   1.0000
   2.750   0.4240   0.05929   0.05012  -0.0238   0.4410   1.0000
   3.000   0.4234   0.06235   0.05313  -0.0233   0.4432   1.0000
   3.250   0.4284   0.06510   0.05583  -0.0224   0.4453   1.0000
   3.500   0.2174   0.07510   0.06603  -0.0239   0.6018   1.0000
   3.750   0.2330   0.07701   0.06784  -0.0230   0.5901   1.0000
   4.000   0.2326   0.07858   0.06930  -0.0211   0.5810   1.0000
   4.250   0.2501   0.08069   0.07133  -0.0204   0.5697   1.0000
   4.500   0.2489   0.08216   0.07269  -0.0185   0.5597   1.0000
   4.750   0.2709   0.08465   0.07511  -0.0182   0.5488   1.0000
   5.000   0.2667   0.08594   0.07631  -0.0164   0.5390   1.0000
   5.500   0.3044   0.09180   0.08202  -0.0161   0.5242   1.0000
   5.750   0.2965   0.09194   0.08209  -0.0141   0.5111   1.0000
   6.000   0.3385   0.09715   0.08726  -0.0153   0.5054   1.0000
   6.250   0.3121   0.09593   0.08596  -0.0127   0.4931   1.0000
   6.500   0.3413   0.09966   0.08964  -0.0131   0.4867   1.0000
   6.750   0.3313   0.10062   0.09054  -0.0120   0.4793   1.0000
   7.000   0.3436   0.10271   0.09258  -0.0116   0.4701   1.0000
   7.250   0.3841   0.10836   0.09820  -0.0125   0.4652   1.0000
   7.500   0.3560   0.10692   0.09670  -0.0108   0.4546   1.0000
   7.750   0.3810   0.11035   0.10011  -0.0109   0.4475   1.0000
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