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.

(s9037-il) S9037 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane Max thickness 9% at 28.5% chord Max camber 3.3% at 42.4% chord Max Cl/Cd 34.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s9000-il) S9000 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 28.2% chord Max camber 2.1% at 44.8% chord Max Cl/Cd 34.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe532-il) GOE 532 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 532 airfoil Max thickness 12.5% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 34.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe393-il) GOE 393 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 34.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s6063-il) S6063 7.05%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6063 low Reynolds number airfoil Max thickness 7% at 29.4% chord Max camber 1.3% at 43.8% chord Max Cl/Cd 34.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(rhodesg30-il) Rhode St. Genese 30		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 30 airfoil Max thickness 9.7% at 30% chord Max camber 3.2% at 40% chord Max Cl/Cd 34.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe585-il) GOE 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 585 airfoil Max thickness 8.2% at 20% chord Max camber 3.4% at 40% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca2412-il) NACA 2412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2412 airfoil Max thickness 12% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh201-il) MH 201 13.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sa7038-il) SA7038		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7038 Max thickness 9.2% at 28.5% chord Max camber 3% at 42.5% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database