Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(n0012-il) NACA 0012 AIRFOILS		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 45.9 at Re# 200,000 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
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Max Cl/Cd 45.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Max Cl/Cd 45.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(drgnfly-il) DRAGONFLY CANARD		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dragonfly Canard airfoil Max thickness 19.3% at 37.6% chord Max camber 6.6% at 40.9% chord Max Cl/Cd 45.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m3-il) NACA M3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 45.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(nacam3-il) NACA M3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 45.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n13-il) N-13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord Max Cl/Cd 45.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n64212mb-il) NACA 64(1)-212 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Max Cl/Cd 45.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe13k-il) GOE 13K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 13K airfoil Max thickness 14.8% at 50% chord Max camber 5.5% at 60% chord Max Cl/Cd 45.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(j5012-il) J5012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jef Raskin (originator of the Apple Macintosh Project) J5012 airfoil Max thickness 12% at 34.5% chord Max camber 0% at 83.5% chord Max Cl/Cd 45.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database