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MH 121 8.76% (mh121-il)

MH 121 8.76% - Martin Hepperle MH 121 for tip section of a propeller


Airfoil mh121-il
Details Dat file Parser  
(mh121-il) MH 121 8.76%
Martin Hepperle MH 121 for tip section of a propeller
Max thickness 8.8% at 37.9% chord.
Max camber 3% at 62.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 121  8.76% 
  1.00000000  0.00000000
  0.99673797  0.00085150
  0.98753891  0.00352659
  0.97341690  0.00772780
  0.95474371  0.01263896
  0.93134847  0.01790405
  0.90336313  0.02365142
  0.87128597  0.02989427
  0.83565023  0.03648448
  0.79703464  0.04321792
  0.75603131  0.04973358
  0.71304543  0.05555745
  0.66827638  0.06036372
  0.62194317  0.06401863
  0.57428530  0.06650354
  0.52567223  0.06795023
  0.47661830  0.06843706
  0.42763480  0.06800259
  0.37923177  0.06668134
  0.33191002  0.06451917
  0.28616015  0.06156216
  0.24245302  0.05787462
  0.20124046  0.05352195
  0.16294421  0.04858951
  0.12795980  0.04316386
  0.09664381  0.03735173
  0.06932353  0.03126124
  0.04628547  0.02501144
  0.02775970  0.01870368
  0.01389310  0.01249514
  0.00479068  0.00656288
  0.00242620  0.00426765
  0.00117353  0.00270737
  0.00034693  0.00128230
  0.00005495  0.00042685
  0.00003105 -0.00030958
  0.00034436 -0.00099334
  0.00096901 -0.00170880
  0.00235716 -0.00281100
  0.00423630 -0.00393734
  0.00933332 -0.00621728
  0.02209641 -0.00995442
  0.03998520 -0.01325767
  0.06291471 -0.01615295
  0.09059174 -0.01867245
  0.12265356 -0.02079508
  0.15869966 -0.02247370
  0.19829137 -0.02364451
  0.24095146 -0.02422833
  0.28616832 -0.02405832
  0.33359195 -0.02289076
  0.38302143 -0.02067641
  0.43418030 -0.01753351
  0.48677017 -0.01369298
  0.54032759 -0.00956165
  0.59417530 -0.00548781
  0.64758980 -0.00173194
  0.69981606  0.00149413
  0.75008228  0.00402963
  0.79761536  0.00577419
  0.84165879  0.00668489
  0.88148980  0.00678588
  0.91643751  0.00616323
  0.94589961  0.00496405
  0.96933923  0.00339929
  0.98632029  0.00178108
  0.99657544  0.00050254
  1.00000000  0.00000000
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Polars for MH 121 8.76% (mh121-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh121-il50,000931.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh121-il50,000535.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh121-il100,000953.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh121-il100,000557.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh121-il200,000984 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   mh121-il200,000582.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh121-il500,0009125.8 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   mh121-il500,0005107.8 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh121-il1,000,0009139.1 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   mh121-il1,000,0005117.7 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
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