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MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 92 15.49% (mh92-il)
Reynolds number: 100,000
Max Cl/Cd: 33.81 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh92-il-100000.txt
Download as CSV file: xf-mh92-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 92  15.49%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5211   0.11081   0.10631   0.0072   1.0000   0.1514
 -10.500  -0.7073   0.06168   0.05671  -0.0264   1.0000   0.0699
 -10.250  -0.7454   0.06621   0.06110  -0.0233   1.0000   0.0725
 -10.000  -0.7786   0.06110   0.05563  -0.0203   1.0000   0.0659
  -9.750  -0.8205   0.05589   0.04963  -0.0151   1.0000   0.0596
  -9.500  -0.8118   0.05197   0.04560  -0.0141   1.0000   0.0580
  -9.250  -0.8117   0.04811   0.04137  -0.0119   1.0000   0.0559
  -9.000  -0.8235   0.04472   0.03694  -0.0069   1.0000   0.0527
  -8.750  -0.8060   0.04168   0.03367  -0.0060   1.0000   0.0523
  -8.500  -0.7881   0.03890   0.03064  -0.0049   1.0000   0.0521
  -8.250  -0.7681   0.03648   0.02798  -0.0039   1.0000   0.0521
  -8.000  -0.7472   0.03433   0.02553  -0.0030   1.0000   0.0525
  -7.750  -0.7207   0.03187   0.02308  -0.0031   1.0000   0.0537
  -7.500  -0.6991   0.03045   0.02174  -0.0026   1.0000   0.0565
  -7.250  -0.6876   0.02942   0.02064  -0.0003   1.0000   0.0583
  -7.000  -0.6889   0.02888   0.01993   0.0040   1.0000   0.0601
  -6.500  -0.6218   0.02575   0.01695   0.0007   0.9877   0.0684
  -6.250  -0.5733   0.02381   0.01523  -0.0037   0.9765   0.0807
  -6.000  -0.5314   0.02186   0.01353  -0.0071   0.9634   0.1043
  -5.750  -0.5127   0.01888   0.01173  -0.0072   0.9461   0.2282
  -5.500  -0.5001   0.01742   0.01133  -0.0050   0.9278   0.4210
  -5.250  -0.4816   0.01716   0.01132  -0.0028   0.9093   0.4986
  -5.000  -0.4630   0.01711   0.01139  -0.0001   0.8919   0.5553
  -4.750  -0.4431   0.01721   0.01162   0.0027   0.8757   0.6032
  -4.500  -0.4233   0.01745   0.01189   0.0058   0.8605   0.6449
  -4.250  -0.4013   0.01787   0.01232   0.0087   0.8450   0.6807
  -4.000  -0.3770   0.01844   0.01287   0.0113   0.8296   0.7110
  -3.750  -0.3497   0.01905   0.01341   0.0134   0.8148   0.7346
  -3.500  -0.3204   0.01963   0.01387   0.0152   0.8004   0.7535
  -3.250  -0.2914   0.02015   0.01424   0.0168   0.7869   0.7707
  -3.000  -0.2626   0.02061   0.01454   0.0185   0.7736   0.7869
  -2.750  -0.2336   0.02103   0.01483   0.0197   0.7586   0.8028
  -2.500  -0.1908   0.02165   0.01528   0.0189   0.7436   0.8126
  -2.250  -0.1566   0.02196   0.01543   0.0190   0.7296   0.8251
  -2.000  -0.1277   0.02212   0.01540   0.0200   0.7172   0.8393
  -1.750  -0.0786   0.02243   0.01554   0.0174   0.7016   0.8472
  -1.500  -0.0433   0.02253   0.01551   0.0166   0.6864   0.8594
  -1.250  -0.0151   0.02258   0.01543   0.0170   0.6725   0.8737
  -1.000   0.0377   0.02265   0.01531   0.0132   0.6574   0.8804
  -0.750   0.0682   0.02259   0.01507   0.0132   0.6450   0.8933
  -0.500   0.1123   0.02258   0.01494   0.0105   0.6291   0.9030
  -0.250   0.1499   0.02251   0.01477   0.0088   0.6141   0.9140
   0.000   0.1822   0.02248   0.01461   0.0079   0.6006   0.9266
   0.250   0.2277   0.02229   0.01426   0.0047   0.5867   0.9358
   0.500   0.2661   0.02209   0.01392   0.0027   0.5733   0.9464
   0.750   0.3024   0.02197   0.01373   0.0008   0.5587   0.9576
   1.000   0.3454   0.02171   0.01339  -0.0024   0.5444   0.9670
   1.250   0.3866   0.02144   0.01299  -0.0053   0.5314   0.9760
   1.500   0.4267   0.02114   0.01255  -0.0080   0.5193   0.9851
   1.750   0.4684   0.02089   0.01228  -0.0114   0.5052   0.9937
   2.000   0.5078   0.02063   0.01197  -0.0143   0.4925   1.0000
   2.250   0.5278   0.02063   0.01182  -0.0133   0.4839   1.0000
   2.500   0.5485   0.02078   0.01201  -0.0128   0.4728   1.0000
   2.750   0.5688   0.02084   0.01192  -0.0118   0.4649   1.0000
   3.000   0.5896   0.02103   0.01219  -0.0113   0.4541   1.0000
   3.250   0.6103   0.02117   0.01221  -0.0104   0.4464   1.0000
   3.500   0.6310   0.02140   0.01250  -0.0098   0.4365   1.0000
   3.750   0.6520   0.02157   0.01255  -0.0089   0.4292   1.0000
   4.000   0.6725   0.02188   0.01298  -0.0083   0.4197   1.0000
   4.250   0.6939   0.02205   0.01298  -0.0073   0.4133   1.0000
   4.500   0.7137   0.02247   0.01356  -0.0066   0.4037   1.0000
   4.750   0.7350   0.02265   0.01363  -0.0057   0.3971   1.0000
   5.000   0.7544   0.02317   0.01430  -0.0049   0.3888   1.0000
   5.250   0.7750   0.02345   0.01453  -0.0039   0.3819   1.0000
   5.500   0.7945   0.02394   0.01507  -0.0030   0.3750   1.0000
   5.750   0.8133   0.02439   0.01559  -0.0019   0.3673   1.0000
   6.000   0.8348   0.02469   0.01573  -0.0009   0.3619   1.0000
   6.250   0.8502   0.02550   0.01679   0.0003   0.3542   1.0000
   6.500   0.8696   0.02586   0.01713   0.0015   0.3480   1.0000
   6.750   0.8877   0.02647   0.01776   0.0027   0.3421   1.0000
   7.000   0.9023   0.02723   0.01868   0.0042   0.3352   1.0000
   7.250   0.9223   0.02757   0.01896   0.0055   0.3299   1.0000
   7.500   0.9358   0.02849   0.02002   0.0071   0.3239   1.0000
   7.750   0.9493   0.02923   0.02088   0.0089   0.3176   1.0000
   8.000   0.9701   0.02954   0.02110   0.0101   0.3126   1.0000
   8.250   0.9783   0.03071   0.02247   0.0123   0.3069   1.0000
   8.500   0.9895   0.03151   0.02338   0.0144   0.3009   1.0000
   8.750   1.0117   0.03173   0.02348   0.0155   0.2960   1.0000
   9.000   1.0149   0.03310   0.02508   0.0183   0.2906   1.0000
   9.250   1.0226   0.03402   0.02614   0.0207   0.2848   1.0000
   9.500   1.0476   0.03409   0.02607   0.0215   0.2798   1.0000
   9.750   1.0473   0.03565   0.02785   0.0245   0.2747   1.0000
  10.000   1.0505   0.03685   0.02921   0.0271   0.2691   1.0000
  10.250   1.0793   0.03677   0.02900   0.0276   0.2639   1.0000
  10.500   1.0769   0.03853   0.03095   0.0304   0.2591   1.0000
  10.750   1.0705   0.04040   0.03304   0.0333   0.2538   1.0000
  11.000   1.1066   0.03993   0.03244   0.0331   0.2482   1.0000
  11.250   1.1017   0.04197   0.03465   0.0356   0.2438   1.0000
  11.500   1.0632   0.04561   0.03858   0.0399   0.2399   1.0000
  11.750   1.0245   0.04949   0.04259   0.0429   0.2367   1.0000
  12.000   0.9548   0.05778   0.05101   0.0425   0.2335   1.0000
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