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.

(goe623-il) GOE 623 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 623 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 40% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe368-il) GOE 368 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 368 airfoil Max thickness 7.7% at 14.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag16-il) AG16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG16 airfoil Max thickness 7.1% at 23.4% chord Max camber 1.9% at 46.9% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m7-il) NACA M7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-7 airfoil Max thickness 6.2% at 40% chord Max camber 4.9% at 30% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s2062-il) S2062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2062 low Reynolds number airfoil Max thickness 8% at 30.1% chord Max camber 1.5% at 49.6% chord Max Cl/Cd 36 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe124-il) GOE 124 (MVA H.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 124 (MVA H.4) airfoil Max thickness 7.9% at 29.9% chord Max camber 5.6% at 39.9% chord Max Cl/Cd 35.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag25-il) AG25 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG25 airfoil used on the Bubble Dancer R/C DLG Max thickness 7.6% at 24.7% chord Max camber 2.4% at 45.4% chord Max Cl/Cd 35.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq2511-il) HQ 2.5/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 2.5% at 50% chord Max Cl/Cd 35.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database