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

MH 38 9.68% (mh38-il)

MH 38 9.68% - Martin Hepperle MH 38 for Endurance Model


Airfoil mh38-il
Details Dat file Parser  
(mh38-il) MH 38 9.68%
Martin Hepperle MH 38 for Endurance Model
Max thickness 9.7% at 31.6% chord.
Max camber 3.9% at 45.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 38  9.68% 
  1.00000000  0.00000000
  0.99681503  0.00052829
  0.98744069  0.00206411
  0.97219660  0.00461800
  0.95140806  0.00820800
  0.92548959  0.01281789
  0.89490506  0.01838273
  0.86016416  0.02479642
  0.82181533  0.03191761
  0.78043788  0.03956173
  0.73663624  0.04751042
  0.69102740  0.05547946
  0.64418318  0.06313426
  0.59661875  0.07011860
  0.54875352  0.07607236
  0.50090364  0.08072602
  0.45336696  0.08391210
  0.40640999  0.08556514
  0.36036364  0.08573940
  0.31562154  0.08448700
  0.27256521  0.08186533
  0.23156049  0.07795837
  0.19296831  0.07288249
  0.15714479  0.06675919
  0.12440457  0.05971034
  0.09500846  0.05189461
  0.06919502  0.04351376
  0.04717790  0.03479969
  0.02915078  0.02601488
  0.01528686  0.01746260
  0.00575479  0.00948521
  0.00235064  0.00541874
  0.00111503  0.00342820
  0.00031376  0.00160406
  0.00004242  0.00050128
  0.00003977 -0.00047153
  0.00036581 -0.00138795
  0.00098926 -0.00233639
  0.00235538 -0.00378184
  0.00418802 -0.00522915
  0.00770050 -0.00733786
  0.01930582 -0.01179167
  0.03580768 -0.01540495
  0.05722344 -0.01796634
  0.08354806 -0.01940709
  0.11472174 -0.01979314
  0.15054213 -0.01929586
  0.19065718 -0.01808367
  0.23464739 -0.01630031
  0.28202506 -0.01409517
  0.33225215 -0.01160078
  0.38474591 -0.00895640
  0.43888457 -0.00628764
  0.49401514 -0.00372487
  0.54945063 -0.00138348
  0.60447998  0.00063604
  0.65838377  0.00226561
  0.71044473  0.00346256
  0.75997115  0.00422322
  0.80630433  0.00456190
  0.84883284  0.00452284
  0.88699574  0.00415677
  0.92028513  0.00353829
  0.94826245  0.00274890
  0.97054484  0.00186730
  0.98678139  0.00099194
  0.99667312  0.00027913
  1.00000000  0.00000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

PSU 94-097 (AIAA 2001-2478)PreviewDetails
MH 116 9.84%PreviewDetails
DAE-51 AIRFOILPreviewDetails
E392 (10.15%)PreviewDetails
GOE 602 MOD. AIRFOILPreviewDetails
S4062-095-87PreviewDetails
GOE 596 AIRFOILPreviewDetails
S4061-096-84PreviewDetails
GOE 115 (MVA MK.2) AIRFOILPreviewDetails
FX 63-100 AIRFOILPreviewDetails

Polars for MH 38 9.68% (mh38-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh38-il50,000937.7 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh38-il50,000537.8 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   mh38-il100,000961.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh38-il100,000561.6 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   mh38-il200,000986.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh38-il200,000585.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   mh38-il500,0009122.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   mh38-il500,0005114.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh38-il1,000,0009149.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mh38-il1,000,0005133.9 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit