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

Airfoil database list (M).

MH 81 13% to MUE 139

Page 5 of 5     1 2 3 4 5     Next

(mh81-il) MH 81 13%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 81  13%Martin Hepperle MH 81 for flying wings (hang glider)
Max thickness 12.9% at 25.4% chord
Max camber 3.3% at 25.4% chord
Source UIUC Airfoil Coordinates Database

(mh82-il) MH 82 13.31%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 82  13.31%Martin Hepperle MH 82 for flying wings (hang glider)
Max thickness 13.3% at 24.6% chord
Max camber 3.9% at 24.6% chord
Source UIUC Airfoil Coordinates Database

(mh83-il) MH 83 13.29%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 83  13.29%Martin Hepperle MH 83 for flying wings (hang glider)
Max thickness 13.3% at 20.6% chord
Max camber 4.5% at 32.6% chord
Source UIUC Airfoil Coordinates Database

(mh84-il) MH 84 13.69%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 84  13.69%Martin Hepperle MH 84 for flying wings (hang glider)
Max thickness 13.7% at 21.5% chord
Max camber 4.1% at 36.6% chord
Source UIUC Airfoil Coordinates Database

(mh91-il) MH 91 14.98%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 91  14.98%Martin Hepperle MH 91 parafoil
Max thickness 15% at 27.3% chord
Max camber 1.4% at 18.7% chord
Source UIUC Airfoil Coordinates Database

(mh92-il) MH 92 15.49%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 92  15.49%Martin Hepperle MH 92 parafoil
Max thickness 15.5% at 27.4% chord
Max camber 1.4% at 15.1% chord
Source UIUC Airfoil Coordinates Database

(mh93-il) MH 93 15.98%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 93  15.98%Martin Hepperle MH 93 parafoil
Max thickness 16% at 27.6% chord
Max camber 1.4% at 15.2% chord
Source UIUC Airfoil Coordinates Database

(mh94-il) MH 94 16.03%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 94  16.03%Martin Hepperle MH 94 parafoil
Max thickness 16% at 34.1% chord
Max camber 1.3% at 74.1% chord
Source UIUC Airfoil Coordinates Database

(mh95-il) MH 95 15.86%

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MH 95  15.86%Martin Hepperle MH 95 parafoil
Max thickness 15.8% at 33.6% chord
Max camber 0.9% at 81.6% chord
Source UIUC Airfoil Coordinates Database

(miley-il) MILEY M06-13-128

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MILEY M06-13-128Miley MO6-13-128 airfoil
Max thickness 12.9% at 35% chord
Max camber 4.9% at 35% chord
Source UIUC Airfoil Coordinates Database

(mrc-16-il) MRC-16

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MRC-16Drela MRC-16
Max thickness 13.9% at 34.6% chord
Max camber 3% at 40.3% chord
Source UIUC Airfoil Coordinates Database

(mrc-20-il) MRC-20

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MRC-20Drela MRC-20
Max thickness 15.6% at 38.2% chord
Max camber 2.9% at 48% chord
Source UIUC Airfoil Coordinates Database

(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NASA/LANGLEY MS(1)-0313 AIRFOILNASA/Langley MS(1)-0313 general aviation airfoil (buggy
Max thickness 13.1% at 37.5% chord
Max camber 1.8% at 67.5% chord
Source UIUC Airfoil Coordinates Database

(ms317-il) NASA/LANGLEY MS(1)-0317 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
NASA/LANGLEY MS(1)-0317 AIRFOILNASA/Langley MS(1)-0317 general aviation airfoil
Max thickness 17% at 37.5% chord
Max camber 1.7% at 72.5% chord
Source UIUC Airfoil Coordinates Database

(mue139-il) MUE 139

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
MUE 139MUE 139 airfoil
Max thickness 13.9% at 22.2% chord
Max camber 4.7% at 30.9% chord
Source UIUC Airfoil Coordinates Database
Page 5 of 5     1 2 3 4 5     Next

Please see the source web site or designer for any license conditions.