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.

(pw98mod-pw) PW98-mod		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.4% at 27.5% chord Max camber 1.8% at 27.5% chord Max Cl/Cd 45.3 at Re# 100,000 Source RC Groups
(rhodesg32-il) Rhode St. Genese 32		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hor04-il) ONERA HOR04 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe229-il) GOE 229 (MVA H.39) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 229 (MVA H.39) airfoil Max thickness 19.3% at 29% chord Max camber 5.9% at 49.1% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe404-il) GOE 404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(m24-il) NACA M24 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa33-il) USA 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s1221-il) S1221 w/o flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah79k132-il) AH 79-K-132/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s8038-il) S8038 (13%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8038 (13%) low Reynolds number airfoil Max thickness 13% at 32.9% chord Max camber 0.6% at 40.1% chord Max Cl/Cd 45.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database