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.

(goe496-il) GOE 496 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 496 airfoil Max thickness 10% at 30% chord Max camber 5% at 50% chord Max Cl/Cd 124.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh113-il) MH 113 14.62%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 113 for a propeller for ultralight Max thickness 14.7% at 29.7% chord Max camber 6.4% at 47.7% chord Max Cl/Cd 124.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s4158-il) S4158		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4158 low Reynolds number airfoil Max thickness 10.9% at 35.3% chord Max camber 3.7% at 44.7% chord Max Cl/Cd 124.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(la203a-il) DOUGLAS LA203A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord Max Cl/Cd 124 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx62k131-il) WORTMANN FX 62-K-131 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 62-K-131/17 airfoil Max thickness 13.1% at 40.2% chord Max camber 3.9% at 53.3% chord Max Cl/Cd 124 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(uag8814320-il) UAG 88-143/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	UAG 88-143/20 airfoil Max thickness 14.3% at 43.5% chord Max camber 6.2% at 46.7% chord Max Cl/Cd 123.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf32-il) RAF 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-32 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 50% chord Max Cl/Cd 123.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(gm15sm-il) GM15 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gilbert Morris GM15 F1C class free flight flapper airfoil Max thickness 6.7% at 20.5% chord Max camber 4.8% at 49.3% chord Max Cl/Cd 123.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sg6042-il) SG6042		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6042 wind turbine airfoil (high L/D) Max thickness 10% at 33.5% chord Max camber 3.3% at 51.5% chord Max Cl/Cd 123.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq358-il) HQ 3.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 123.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database