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

MH 45 9.85% (mh45-il)

MH 45 9.85% - Martin Hepperle MH 45 for flying wings


Airfoil mh45-il
Details Dat file Parser  
(mh45-il) MH 45 9.85%
Martin Hepperle MH 45 for flying wings
Max thickness 9.8% at 26.9% chord.
Max camber 1.7% at 36.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MH 45  9.85% 
  1.00000000  0.00000000
  0.99669413 -0.00009724
  0.98669781 -0.00019095
  0.97014283  0.00019409
  0.94748143  0.00135847
  0.91919309  0.00340462
  0.88577724  0.00640631
  0.84779269  0.01043465
  0.80595479  0.01555735
  0.76114118  0.02164179
  0.71412902  0.02832714
  0.66556275  0.03522557
  0.61598156  0.04192939
  0.56581124  0.04811779
  0.51545926  0.05355525
  0.46531057  0.05809451
  0.41579675  0.06166870
  0.36739295  0.06421657
  0.32056390  0.06566967
  0.27575978  0.06596488
  0.23337160  0.06502718
  0.19371735  0.06284772
  0.15710619  0.05947508
  0.12382631  0.05499062
  0.09414950  0.04950187
  0.06832228  0.04312532
  0.04653066  0.03596944
  0.02886429  0.02820312
  0.01538529  0.02006247
  0.00606648  0.01189423
  0.00125239  0.00490321
  0.00045775  0.00277441
  0.00005213  0.00080294
  0.00001426 -0.00039622
  0.00021828 -0.00145465
  0.00074788 -0.00243613
  0.00159709 -0.00343572
  0.00334092 -0.00496578
  0.00559484 -0.00653095
  0.01774266 -0.01220386
  0.03414149 -0.01725442
  0.05524391 -0.02190990
  0.08078000 -0.02593921
  0.11057454 -0.02909277
  0.14453398 -0.03127840
  0.18244547 -0.03254149
  0.22401044 -0.03295264
  0.26884085 -0.03262660
  0.31647130 -0.03166069
  0.36640050 -0.03015443
  0.41809871 -0.02821510
  0.47098505 -0.02597804
  0.52443625 -0.02355316
  0.57780845 -0.02104980
  0.63044525 -0.01854489
  0.68169412 -0.01611128
  0.73091369 -0.01378344
  0.77750335 -0.01158878
  0.82090623 -0.00954711
  0.86058868 -0.00769696
  0.89604838 -0.00604251
  0.92683839 -0.00458535
  0.95257077 -0.00330256
  0.97292132 -0.00217128
  0.98768944 -0.00112550
  0.99683205 -0.00030439
  1.00000000  0.00000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

MH 44 9.66%PreviewDetails
MH 60 10.08%PreviewDetails
S4095 (designed for the E-flite UMXPreviewDetails
S4094 (root airfoil designed for andPreviewDetails
S5010PreviewDetails
MH 62 9.3%PreviewDetails
MH 61 10.26%PreviewDetails
RAF 28 AIRFOILPreviewDetails
E221 (9.39%)PreviewDetails
RG 14 10% AIRFOILPreviewDetails

Polars for MH 45 9.85% (mh45-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mh45-il50,000927.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh45-il50,000532.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mh45-il100,000944.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   mh45-il100,000545.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh45-il200,000960.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   mh45-il200,000558.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh45-il500,000981.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh45-il500,000575.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mh45-il1,000,000995.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mh45-il1,000,000588.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit