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.

(vr14-il) BOEING-VERTOL VR-14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-14 rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.7% at 20% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe535-il) GOE 535 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 535 airfoil Max thickness 16.1% at 20% chord Max camber 5.8% at 50% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e221-il) E221 (9.39%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E221 low Reynolds number airfoil Max thickness 9.4% at 28.1% chord Max camber 1.6% at 32.6% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe629-il) GOE 629 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 629 airfoil Max thickness 13.6% at 29.4% chord Max camber 2.8% at 39.4% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq3514-il) HQ 3.5/14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e209-il) E209 (13.72%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E209 low Reynolds number airfoil Max thickness 13.7% at 33.8% chord Max camber 1.6% at 48.1% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(r140sm-il) R140 12.04% (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord Max camber 0.4% at 39.3% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe677-il) GOE 677 (= M 6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 677 (= M 6) airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database