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MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 46 9.1% (mh46-il)
Reynolds number: 200,000
Max Cl/Cd: 61.77 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh46-il-200000.txt
Download as CSV file: xf-mh46-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 46  9.1%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5399   0.11127   0.10784   0.0065   1.0000   0.0389
  -9.750  -0.5392   0.10704   0.10364   0.0038   1.0000   0.0403
  -9.500  -0.5442   0.10217   0.09883  -0.0017   1.0000   0.0420
  -9.250  -0.4711   0.09023   0.08721  -0.0054   1.0000   0.0443
  -9.000  -0.4653   0.08656   0.08355  -0.0055   1.0000   0.0453
  -8.750  -0.4631   0.08251   0.07952  -0.0065   1.0000   0.0464
  -8.500  -0.4638   0.07807   0.07510  -0.0081   1.0000   0.0474
  -8.250  -0.4674   0.07326   0.07033  -0.0102   1.0000   0.0484
  -8.000  -0.4737   0.06817   0.06527  -0.0130   1.0000   0.0492
  -7.750  -0.4859   0.06250   0.05965  -0.0170   1.0000   0.0501
  -7.500  -0.5030   0.05639   0.05355  -0.0221   1.0000   0.0502
  -7.250  -0.5133   0.04996   0.04700  -0.0260   1.0000   0.0514
  -6.250  -0.5407   0.03151   0.02596  -0.0260   1.0000   0.0222
  -6.000  -0.5212   0.02887   0.02311  -0.0248   1.0000   0.0203
  -5.750  -0.5059   0.02554   0.01938  -0.0230   1.0000   0.0194
  -5.500  -0.4896   0.02301   0.01647  -0.0209   1.0000   0.0188
  -5.250  -0.4746   0.02104   0.01422  -0.0185   1.0000   0.0186
  -5.000  -0.4612   0.01951   0.01247  -0.0158   1.0000   0.0186
  -4.750  -0.4485   0.01826   0.01103  -0.0131   1.0000   0.0190
  -4.500  -0.4238   0.01699   0.00960  -0.0125   0.9972   0.0204
  -4.250  -0.3864   0.01530   0.00785  -0.0147   0.9898   0.0250
  -4.000  -0.3466   0.01393   0.00643  -0.0171   0.9830   0.0393
  -3.750  -0.3123   0.01204   0.00525  -0.0190   0.9745   0.1653
  -3.500  -0.2721   0.01126   0.00491  -0.0220   0.9682   0.2760
  -3.250  -0.2368   0.01076   0.00462  -0.0237   0.9584   0.3572
  -3.000  -0.2044   0.01028   0.00445  -0.0247   0.9481   0.4475
  -2.750  -0.1748   0.00988   0.00431  -0.0248   0.9373   0.5300
  -2.500  -0.1487   0.00953   0.00419  -0.0241   0.9258   0.6071
  -2.250  -0.1257   0.00917   0.00410  -0.0224   0.9141   0.6887
  -2.000  -0.1022   0.00882   0.00403  -0.0205   0.9018   0.7816
  -1.750  -0.0555   0.00862   0.00400  -0.0233   0.8927   0.8861
  -1.500   0.0030   0.00864   0.00392  -0.0287   0.8851   0.9420
  -1.250   0.0533   0.00872   0.00384  -0.0328   0.8744   0.9721
  -1.000   0.1057   0.00874   0.00371  -0.0377   0.8629   0.9952
  -0.750   0.1351   0.00870   0.00354  -0.0381   0.8487   1.0000
  -0.500   0.1556   0.00870   0.00340  -0.0365   0.8342   1.0000
  -0.250   0.1770   0.00871   0.00330  -0.0351   0.8200   1.0000
   0.000   0.1991   0.00874   0.00322  -0.0338   0.8059   1.0000
   0.250   0.2217   0.00878   0.00316  -0.0325   0.7918   1.0000
   0.500   0.2448   0.00882   0.00310  -0.0314   0.7776   1.0000
   0.750   0.2683   0.00887   0.00306  -0.0303   0.7633   1.0000
   1.000   0.2920   0.00893   0.00303  -0.0293   0.7487   1.0000
   1.250   0.3161   0.00899   0.00302  -0.0283   0.7337   1.0000
   1.500   0.3405   0.00905   0.00304  -0.0275   0.7176   1.0000
   1.750   0.3650   0.00912   0.00305  -0.0266   0.7012   1.0000
   2.000   0.3897   0.00920   0.00306  -0.0258   0.6845   1.0000
   2.250   0.4144   0.00928   0.00308  -0.0249   0.6675   1.0000
   2.500   0.4392   0.00938   0.00314  -0.0241   0.6502   1.0000
   2.750   0.4642   0.00948   0.00321  -0.0234   0.6309   1.0000
   3.000   0.4891   0.00960   0.00327  -0.0227   0.6119   1.0000
   3.250   0.5141   0.00973   0.00337  -0.0219   0.5917   1.0000
   3.500   0.5391   0.00988   0.00349  -0.0212   0.5709   1.0000
   3.750   0.5641   0.01005   0.00362  -0.0206   0.5490   1.0000
   4.000   0.5888   0.01026   0.00376  -0.0198   0.5270   1.0000
   4.250   0.6137   0.01046   0.00394  -0.0192   0.5028   1.0000
   4.500   0.6383   0.01070   0.00414  -0.0185   0.4784   1.0000
   4.750   0.6628   0.01096   0.00439  -0.0178   0.4532   1.0000
   5.000   0.6871   0.01125   0.00464  -0.0171   0.4264   1.0000
   5.250   0.7112   0.01156   0.00491  -0.0164   0.3981   1.0000
   5.500   0.7351   0.01190   0.00521  -0.0157   0.3680   1.0000
   5.750   0.7585   0.01230   0.00554  -0.0150   0.3359   1.0000
   6.000   0.7816   0.01274   0.00595  -0.0143   0.3014   1.0000
   6.250   0.8042   0.01327   0.00638  -0.0135   0.2658   1.0000
   6.500   0.8265   0.01384   0.00686  -0.0128   0.2285   1.0000
   6.750   0.8481   0.01451   0.00742  -0.0120   0.1909   1.0000
   7.000   0.8688   0.01531   0.00807  -0.0112   0.1528   1.0000
   7.250   0.8882   0.01629   0.00886  -0.0102   0.1137   1.0000
   7.500   0.9061   0.01751   0.00993  -0.0090   0.0816   1.0000
   7.750   0.9227   0.01888   0.01126  -0.0075   0.0617   1.0000
   8.000   0.9392   0.02022   0.01261  -0.0060   0.0499   1.0000
   8.250   0.9546   0.02169   0.01408  -0.0044   0.0428   1.0000
   8.500   0.9709   0.02324   0.01577  -0.0027   0.0382   1.0000
   8.750   0.9880   0.02440   0.01698  -0.0015   0.0329   1.0000
   9.000   1.0016   0.02707   0.01975   0.0003   0.0298   1.0000
   9.250   1.0190   0.02811   0.02100   0.0017   0.0260   1.0000
   9.500   1.0335   0.02968   0.02264   0.0031   0.0230   1.0000
   9.750   1.0417   0.03391   0.02715   0.0049   0.0206   1.0000
  10.000   1.0543   0.03441   0.02790   0.0066   0.0178   1.0000
  10.250   1.0633   0.03654   0.03026   0.0084   0.0166   1.0000
  10.500   1.0680   0.03879   0.03277   0.0103   0.0155   1.0000
  10.750   1.0677   0.04137   0.03558   0.0127   0.0151   1.0000
  11.000   1.0627   0.04400   0.03840   0.0150   0.0146   1.0000
  11.250   1.0543   0.04712   0.04177   0.0168   0.0145   1.0000
  11.500   1.0435   0.05057   0.04548   0.0178   0.0146   1.0000
  11.750   1.0306   0.05443   0.04956   0.0179   0.0144   1.0000
  12.000   1.0165   0.05872   0.05407   0.0171   0.0144   1.0000
  12.250   0.9980   0.06407   0.05968   0.0150   0.0147   1.0000
  12.500   0.9781   0.07021   0.06607   0.0117   0.0149   1.0000
  12.750   0.9564   0.07740   0.07348   0.0073   0.0152   1.0000
  13.000   0.9355   0.08508   0.08132   0.0021   0.0151   1.0000
  13.250   0.8937   0.09904   0.09550  -0.0078   0.0165   1.0000
  13.500   0.8554   0.11427   0.11084  -0.0174   0.0179   1.0000
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