Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 25 9.98% (mh25-il)

MH 25 9.98% - Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow)


Airfoil mh25-il
Details Dat file Parser  
(mh25-il) MH 25 9.98%
Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow)
Max thickness 10% at 42.2% chord.
Max camber 1.4% at 42.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 25  9.98% 
  1.00000000  0.00000000
  0.99635051  0.00044823
  0.98573137  0.00204140
  0.96894107  0.00519871
  0.94688038  0.00993961
  0.92037370  0.01596838
  0.89011954  0.02282430
  0.85669024  0.02985118
  0.82021659  0.03629489
  0.78049149  0.04193268
  0.73771056  0.04697095
  0.69238447  0.05145822
  0.64499206  0.05534558
  0.59605623  0.05862203
  0.54612430  0.06122491
  0.49572697  0.06311117
  0.44540326  0.06423869
  0.39569004  0.06458276
  0.34711360  0.06410878
  0.30017618  0.06280648
  0.25536234  0.06066464
  0.21312332  0.05769242
  0.17387529  0.05389664
  0.13797800  0.04931573
  0.10575823  0.04400481
  0.07748459  0.03804852
  0.05338824  0.03155294
  0.03362650  0.02466585
  0.01833367  0.01758842
  0.00757463  0.01059496
  0.00186535  0.00470621
  0.00082048  0.00288211
  0.00018458  0.00120135
  0.00000512  0.00018681
  0.00008206 -0.00069576
  0.00049731 -0.00151394
  0.00123711 -0.00236167
  0.00281860 -0.00367833
  0.00491028 -0.00505231
  0.01668117 -0.01010252
  0.03284835 -0.01455005
  0.05403846 -0.01860966
  0.08010773 -0.02219502
  0.11085035 -0.02530002
  0.14595902 -0.02798038
  0.18500534 -0.03026407
  0.22753533 -0.03213699
  0.27305393 -0.03358921
  0.32106307 -0.03458492
  0.37105343 -0.03513721
  0.42247260 -0.03526852
  0.47472749 -0.03500919
  0.52721868 -0.03435978
  0.57934234 -0.03333837
  0.63049994 -0.03193727
  0.68010142 -0.03016404
  0.72758141 -0.02798673
  0.77240110 -0.02539979
  0.81402717 -0.02225708
  0.85232061 -0.01834465
  0.88735957 -0.01400994
  0.91868469 -0.00982829
  0.94576564 -0.00601403
  0.96822033 -0.00291374
  0.98536058 -0.00093384
  0.99624793 -0.00013682
  1.00000000  0.00000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

HAWKER TEMPEST 96.77% SEMISPANPreviewDetails
NACA 0010-34 a=0.8 c(li)=0.2PreviewDetails
NACA 64A210PreviewDetails
NASA/LANGLEY RC10-64C AIRFOILPreviewDetails
NACA 64-210PreviewDetails
NACA 65-210PreviewDetails
NACA 66-210PreviewDetails
NACA 5-H-10 AIRFOILPreviewDetails
LOCKHEED C-141 BL958.89 AIRFOILPreviewDetails
MH 26 10.99%PreviewDetails

Polars for MH 25 9.98% (mh25-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh25-il50,000934.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh25-il50,000532.9 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh25-il100,000951.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh25-il100,000548 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh25-il200,000970.9 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   mh25-il200,000558.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh25-il500,000978.8 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   mh25-il500,000560.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh25-il1,000,000975 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh25-il1,000,000569.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit