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.

(raf19-il) RAF 19 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-19 airfoil Max thickness 10.5% at 15% chord Max camber 10.1% at 40% chord Max Cl/Cd 48.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(geminism-il) GEMINI (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord Max Cl/Cd 48.6 at Re# 100,000 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 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(amsoil1-il) RUTAN CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ag19-il) AG19		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe147-il) GOE 147 (MVA H.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 147 (MVA H.6) airfoil Max thickness 7.5% at 14.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx63147-il) FX 63-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-147 airfoil Max thickness 14.7% at 33.9% chord Max camber 3.1% at 33.9% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s6063-il) S6063 7.05%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6063 low Reynolds number airfoil Max thickness 7% at 29.4% chord Max camber 1.3% at 43.8% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh112-il) MH 112 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 112 for a propeller for ultralight (root) Max thickness 16.2% at 31.8% chord Max camber 6.7% at 48.5% chord Max Cl/Cd 48.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database