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.

(n24-il) N-24		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-24 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh1070-il) Eh 1.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 1% at 25.9% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e1233-il) EPPLER 1233 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca643218-il) NACA 64(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe683-il) GOE 683 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 683 airfoil Max thickness 19.9% at 30% chord Max camber 3% at 30% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(oa209-il) ONERA OA209 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord Max camber 1.6% at 17.1% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe627-il) GOE 627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 627 airfoil Max thickness 15.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 41.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiim-il) GIII BL430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.2% chord Max camber 1.9% at 25.2% chord Max Cl/Cd 41.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(oaf128-il) OAF128 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF128 Fenestron airfoil Max thickness 12.8% at 23.2% chord Max camber 1% at 43.7% chord Max Cl/Cd 41.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database