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MH 122 9.32% (mh122-il)

MH 122 9.32% - Martin Hepperle MH 122 for tip section of a propeller


Airfoil mh122-il
Details Dat file Parser  
(mh122-il) MH 122 9.32%
Martin Hepperle MH 122 for tip section of a propeller
Max thickness 9.3% at 37.6% chord.
Max camber 3.4% at 64.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 122  9.32% 
  1.00000000  0.00000000
  0.99671214  0.00094088
  0.98747022  0.00387049
  0.97333294  0.00845168
  0.95467462  0.01383235
  0.93131634  0.01964377
  0.90340186  0.02601454
  0.87144348  0.03293587
  0.83598396  0.04024266
  0.79760627  0.04769974
  0.75690321  0.05492294
  0.71426848  0.06140206
  0.66988613  0.06679569
  0.62395310  0.07093837
  0.57667268  0.07381456
  0.52839712  0.07556141
  0.47963722  0.07627364
  0.43090257  0.07598084
  0.38269806  0.07472800
  0.33552389  0.07255182
  0.28986559  0.06950899
  0.24619546  0.06565593
  0.20496074  0.06106904
  0.16658753  0.05582717
  0.13146755  0.05002756
  0.09996656  0.04377019
  0.07240999  0.03717058
  0.04910853  0.03032577
  0.03025979  0.02329407
  0.01595183  0.01621738
  0.00619913  0.00931408
  0.00187285  0.00454079
  0.00082562  0.00276625
  0.00018787  0.00115304
  0.00000613  0.00019275
  0.00007665 -0.00062800
  0.00047684 -0.00137204
  0.00119158 -0.00212801
  0.00271873 -0.00326966
  0.00473455 -0.00442389
  0.00687089 -0.00544602
  0.01857031 -0.00920674
  0.03554803 -0.01248748
  0.05770039 -0.01530320
  0.08473332 -0.01771135
  0.11627469 -0.01969985
  0.15192385 -0.02122964
  0.19123507 -0.02224863
  0.23372869 -0.02267809
  0.27888453 -0.02236014
  0.32635572 -0.02104084
  0.37594698 -0.01868739
  0.42737779 -0.01542955
  0.48033096 -0.01151470
  0.53433027 -0.00734207
  0.58868858 -0.00327108
  0.64266859  0.00044342
  0.69550152  0.00357810
  0.74639759  0.00598101
  0.79456668  0.00754409
  0.83923216  0.00823769
  0.87965251  0.00808441
  0.91513702  0.00718871
  0.94506510  0.00570301
  0.96887829  0.00386172
  0.98612202  0.00200258
  0.99652743  0.00056064
  1.00000000  0.00000000
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Polars for MH 122 9.32% (mh122-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh122-il50,000938 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh122-il50,000538 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh122-il100,000961.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh122-il100,000558.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh122-il200,000990.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh122-il200,000587.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   mh122-il500,0009137.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh122-il500,0005114.9 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   mh122-il1,000,0009161.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh122-il1,000,0005125.1 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
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