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MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 102 16.99% (mh102-il)
Reynolds number: 50,000
Max Cl/Cd: 5.54 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh102-il-50000.txt
Download as CSV file: xf-mh102-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 102  16.99%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2848   0.11661   0.10928  -0.0231   1.0000   0.3323
 -10.500  -0.2986   0.11588   0.10862  -0.0230   1.0000   0.3451
 -10.250  -0.2801   0.11168   0.10439  -0.0223   1.0000   0.3622
 -10.000  -0.2655   0.10791   0.10059  -0.0219   1.0000   0.3772
  -9.750  -0.2616   0.10499   0.09770  -0.0214   1.0000   0.3901
  -9.500  -0.2900   0.10546   0.09831  -0.0201   1.0000   0.4022
  -9.250  -0.2730   0.10191   0.09473  -0.0193   1.0000   0.4206
  -9.000  -0.2555   0.09838   0.09118  -0.0185   1.0000   0.4383
  -8.750  -0.2404   0.09514   0.08793  -0.0178   1.0000   0.4545
  -8.500  -0.2329   0.09249   0.08530  -0.0168   1.0000   0.4688
  -8.250  -0.2339   0.09059   0.08348  -0.0152   1.0000   0.4841
  -8.000  -0.2631   0.09135   0.08442  -0.0114   1.0000   0.4983
  -7.750  -0.4787   0.07910   0.07293  -0.0156   1.0000   0.3268
  -7.500  -0.5089   0.07677   0.07072  -0.0124   1.0000   0.3257
  -7.250  -0.5428   0.07369   0.06775  -0.0100   1.0000   0.3244
  -7.000  -0.5799   0.06957   0.06368  -0.0088   1.0000   0.3234
  -6.750  -0.6176   0.06422   0.05829  -0.0089   1.0000   0.3242
  -6.500  -0.6502   0.05783   0.05165  -0.0104   1.0000   0.3281
  -6.250  -0.6290   0.06008   0.05404  -0.0055   1.0000   0.3390
  -6.000  -0.6029   0.05736   0.05111  -0.0096   0.9903   0.3525
  -5.750  -0.5796   0.05272   0.04603  -0.0167   0.9772   0.3659
  -5.500  -0.5382   0.05217   0.04538  -0.0195   0.9643   0.3790
  -5.250  -0.5023   0.05032   0.04332  -0.0234   0.9516   0.3902
  -5.000  -0.4753   0.04740   0.03998  -0.0282   0.9386   0.4015
  -4.750  -0.4436   0.04688   0.03945  -0.0291   0.9256   0.4105
  -4.500  -0.4179   0.04463   0.03675  -0.0328   0.9131   0.4212
  -4.250  -0.3744   0.04420   0.03632  -0.0354   0.9019   0.4316
  -4.000  -0.3534   0.04268   0.03446  -0.0371   0.8892   0.4414
  -3.750  -0.3252   0.04236   0.03413  -0.0375   0.8773   0.4498
  -3.500  -0.2838   0.04130   0.03279  -0.0413   0.8672   0.4626
  -3.250  -0.2684   0.04107   0.03253  -0.0401   0.8547   0.4707
  -3.000  -0.2355   0.04044   0.03169  -0.0421   0.8446   0.4827
  -2.750  -0.2109   0.04019   0.03135  -0.0423   0.8334   0.4941
  -2.500  -0.1881   0.04001   0.03110  -0.0424   0.8233   0.5048
  -2.250  -0.1575   0.03971   0.03064  -0.0437   0.8135   0.5191
  -2.000  -0.1408   0.03988   0.03082  -0.0425   0.8034   0.5305
  -1.750  -0.1091   0.03976   0.03065  -0.0435   0.7943   0.5458
  -1.500  -0.0951   0.04003   0.03084  -0.0424   0.7850   0.5597
  -1.250  -0.0673   0.04010   0.03089  -0.0428   0.7761   0.5779
  -1.000  -0.0491   0.04047   0.03122  -0.0421   0.7676   0.5956
  -0.750  -0.0325   0.04085   0.03162  -0.0411   0.7589   0.6145
  -0.500  -0.0011   0.04105   0.03189  -0.0413   0.7517   0.6386
  -0.250  -0.0006   0.04188   0.03276  -0.0386   0.7430   0.6575
   0.000   0.0358   0.04196   0.03290  -0.0392   0.7359   0.6926
   0.250   0.0329   0.04297   0.03402  -0.0359   0.7285   0.7169
   0.500   0.0469   0.04349   0.03469  -0.0340   0.7212   0.7553
   0.750   0.0768   0.04369   0.03512  -0.0328   0.7146   0.8139
   1.000   0.0840   0.04485   0.03655  -0.0315   0.7071   0.8825
   1.250   0.2470   0.04602   0.03756  -0.0565   0.6927   1.0000
   1.500   0.2135   0.04712   0.03836  -0.0515   0.6870   1.0000
   1.750   0.2502   0.04780   0.03878  -0.0533   0.6798   1.0000
   2.000   0.2389   0.04968   0.04049  -0.0506   0.6737   1.0000
   2.250   0.2415   0.05129   0.04196  -0.0493   0.6673   1.0000
   2.500   0.2881   0.05204   0.04254  -0.0513   0.6593   1.0000
   2.750   0.2678   0.05438   0.04479  -0.0484   0.6546   1.0000
   3.000   0.2721   0.05617   0.04650  -0.0474   0.6490   1.0000
   3.250   0.3138   0.05719   0.04739  -0.0488   0.6403   1.0000
   3.500   0.3003   0.05959   0.04973  -0.0468   0.6369   1.0000
   3.750   0.3001   0.06172   0.05181  -0.0459   0.6331   1.0000
   4.000   0.3066   0.06384   0.05387  -0.0455   0.6302   1.0000
   4.250   0.3374   0.06534   0.05530  -0.0461   0.6205   1.0000
   4.500   0.2947   0.07040   0.06041  -0.0458   0.6566   1.0000
   4.750   0.3449   0.07052   0.06042  -0.0458   0.6210   1.0000
   5.000   0.3602   0.07335   0.06321  -0.0467   0.6226   1.0000
   5.250   0.2872   0.08050   0.07050  -0.0477   0.7157   1.0000
   5.500   0.2798   0.08060   0.07057  -0.0452   0.7023   1.0000
   5.750   0.2955   0.08297   0.07290  -0.0455   0.6927   1.0000
   6.000   0.3248   0.08578   0.07568  -0.0469   0.6798   1.0000
   6.250   0.3222   0.08687   0.07676  -0.0454   0.6684   1.0000
   6.500   0.3631   0.09119   0.08104  -0.0480   0.6595   1.0000
   6.750   0.3583   0.09160   0.08145  -0.0462   0.6452   1.0000
   7.000   0.3688   0.09407   0.08390  -0.0462   0.6370   1.0000
   7.250   0.3927   0.09674   0.08657  -0.0470   0.6248   1.0000
   7.500   0.3915   0.09826   0.08809  -0.0460   0.6135   1.0000
   7.750   0.4320   0.10269   0.09253  -0.0482   0.6047   1.0000
   8.000   0.4184   0.10309   0.09293  -0.0464   0.5927   1.0000
   8.250   0.4512   0.10742   0.09726  -0.0481   0.5852   1.0000
   8.500   0.4482   0.10826   0.09811  -0.0469   0.5717   1.0000
   8.750   0.4623   0.11152   0.10139  -0.0475   0.5653   1.0000
   9.000   0.4732   0.11350   0.10339  -0.0474   0.5528   1.0000
   9.250   0.4771   0.11596   0.10586  -0.0474   0.5443   1.0000
   9.500   0.4996   0.11900   0.10893  -0.0480   0.5337   1.0000
   9.750   0.4979   0.12117   0.11112  -0.0479   0.5258   1.0000
  10.000   0.5221   0.12445   0.11444  -0.0486   0.5153   1.0000
  10.250   0.5177   0.12637   0.11637  -0.0484   0.5067   1.0000
  10.500   0.5409   0.12977   0.11981  -0.0491   0.4976   1.0000
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