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.

(goe619-il) GOE 619 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 619 airfoil Max thickness 13.7% at 19.5% chord Max camber 4.5% at 49.5% chord Max Cl/Cd 33.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord Max camber 3% at 29% chord Max Cl/Cd 33.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nacacyh-il) NACA CYH		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA CYH airfoil Max thickness 11.7% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 33.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rg14-il) RG 14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 airfoil Max thickness 8.5% at 29.7% chord Max camber 1.6% at 39.2% chord Max Cl/Cd 33.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe180-il) GOE 180 (MVA H.26) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 180 (MVA H.26) airfoil Max thickness 8.7% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sa7035-il) SA7035		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7035 Max thickness 9.2% at 27.9% chord Max camber 2.4% at 41.9% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s2050-il) S2050 8.93%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe711-il) GOE 711 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 711 airfoil Max thickness 14.9% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq2012-il) HQ 2.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database