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MH 200 12.97% (mh200-il)

MH 200 12.97% - Martin Hepperle MH 200 for a canard airplane (main wing)


Airfoil mh200-il
Details Dat file Parser  
(mh200-il) MH 200 12.97%
Martin Hepperle MH 200 for a canard airplane (main wing)
Max thickness 13% at 39.5% chord.
Max camber 2.1% at 49.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 200  12.97% 
  1.00000000  0.00000000
  0.99649500  0.00069704
  0.98645609  0.00294186
  0.97076930  0.00667102
  0.94991971  0.01138589
  0.92401295  0.01684286
  0.89335961  0.02311601
  0.85853187  0.03017901
  0.82013428  0.03788260
  0.77880287  0.04601904
  0.73518677  0.05430353
  0.68993711  0.06238477
  0.64368050  0.06973364
  0.59665380  0.07568313
  0.54874065  0.08004849
  0.50018351  0.08307833
  0.45151296  0.08486339
  0.40319441  0.08541917
  0.35571692  0.08481364
  0.30959347  0.08308417
  0.26530396  0.08025749
  0.22329039  0.07637741
  0.18398182  0.07151905
  0.14780067  0.06574033
  0.11509401  0.05907667
  0.08612403  0.05160462
  0.06110030  0.04344873
  0.04017907  0.03478990
  0.02349151  0.02588057
  0.01117972  0.01702927
  0.00336229  0.00856940
  0.00149051  0.00536311
  0.00057296  0.00310588
  0.00008069  0.00101423
  0.00000589 -0.00025882
  0.00019148 -0.00138414
  0.00072371 -0.00243308
  0.00159345 -0.00350752
  0.00339509 -0.00515747
  0.00573688 -0.00684716
  0.01187173 -0.01031383
  0.02631155 -0.01615513
  0.04570376 -0.02180505
  0.06978199 -0.02703507
  0.09833796 -0.03168592
  0.13110429 -0.03567750
  0.16777438 -0.03894575
  0.20799248 -0.04146594
  0.25136229 -0.04323894
  0.29740143 -0.04430647
  0.34555461 -0.04464846
  0.39530202 -0.04420835
  0.44615731 -0.04298281
  0.49755498 -0.04103403
  0.54885834 -0.03830858
  0.59958021 -0.03466607
  0.64936067 -0.03003127
  0.69802270 -0.02438677
  0.74557328 -0.01813550
  0.79158005 -0.01209878
  0.83516514 -0.00686466
  0.87541871 -0.00275971
  0.91143931  0.00004584
  0.94236314  0.00150090
  0.96729660  0.00170650
  0.98543227  0.00109722
  0.99635903  0.00033296
  1.00000000  0.00000000
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Polars for MH 200 12.97% (mh200-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh200-il50,000933.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   mh200-il50,000532.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   mh200-il100,000953.4 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   mh200-il100,000551 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh200-il200,000976.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   mh200-il200,000566.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh200-il500,000998.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh200-il500,000585.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh200-il1,000,0009117 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh200-il1,000,000593.7 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
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