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

MH 108 11.98% (mh108-il)

MH 108 11.98% - Martin Hepperle MH 108 for stall controlled wind turbines


Airfoil mh108-il
Details Dat file Parser  
(mh108-il) MH 108 11.98%
Martin Hepperle MH 108 for stall controlled wind turbines
Max thickness 11.9% at 22.8% chord.
Max camber 1% at 22.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 108  11.98% 
  1.00000000  0.00000000
  0.99643033  0.00010286
  0.98603763  0.00066669
  0.96947896  0.00192106
  0.94720078  0.00365936
  0.91935509  0.00579598
  0.88623754  0.00850390
  0.84838241  0.01189976
  0.80638582  0.01600336
  0.76089491  0.02078583
  0.71259079  0.02616460
  0.66217346  0.03201092
  0.61034600  0.03815523
  0.55780031  0.04439373
  0.50520434  0.05049864
  0.45319097  0.05622665
  0.40234976  0.06132989
  0.35322031  0.06556690
  0.30628931  0.06870603
  0.26198966  0.07055264
  0.22076101  0.07087754
  0.18280706  0.06932533
  0.14799337  0.06584228
  0.11636066  0.06076102
  0.08817487  0.05435476
  0.06365534  0.04681824
  0.04296243  0.03836070
  0.02617902  0.02924957
  0.01338734  0.01987044
  0.00471080  0.01069468
  0.00213785  0.00668444
  0.00097387  0.00421472
  0.00024125  0.00189559
  0.00001521  0.00045547
  0.00005978 -0.00086338
  0.00043863 -0.00214136
  0.00112303 -0.00347361
  0.00259625 -0.00554510
  0.00455379 -0.00768327
  0.00918245 -0.01162830
  0.02136259 -0.01892355
  0.03811696 -0.02578767
  0.05940336 -0.03194090
  0.08512326 -0.03723697
  0.11512209 -0.04157934
  0.14919903 -0.04492245
  0.18709655 -0.04726839
  0.22848557 -0.04866214
  0.27296544 -0.04915622
  0.32009677 -0.04880995
  0.36940148 -0.04770014
  0.42036942 -0.04591650
  0.47246265 -0.04358113
  0.52506272 -0.04083367
  0.57751487 -0.03773249
  0.62923986 -0.03431645
  0.67967031 -0.03068146
  0.72821823 -0.02692405
  0.77431230 -0.02312859
  0.81740436 -0.01937698
  0.85697399 -0.01574752
  0.89253305 -0.01231192
  0.92362931 -0.00913872
  0.94984553 -0.00626002
  0.97090521 -0.00369000
  0.98661374 -0.00162560
  0.99655052 -0.00038512
  1.00000000  0.00000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 766 AIRFOILPreviewDetails
GOE 767 AIRFOILPreviewDetails
NACA 24112PreviewDetails
NACA 23112PreviewDetails
EH 2.0/12PreviewDetails
MH 106 13.07%PreviewDetails
N-14PreviewDetails
NPL 9626 AIRFOILPreviewDetails
NACA 25112PreviewDetails
EPPLER 485 AIRFOILPreviewDetails

Polars for MH 108 11.98% (mh108-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh108-il50,000916.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh108-il50,000525.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh108-il100,000936.1 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   mh108-il100,000542.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh108-il200,000956.3 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   mh108-il200,000558.5 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh108-il500,000982.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   mh108-il500,000579.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh108-il1,000,0009102 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   mh108-il1,000,000593.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit