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.

(naca2424-il) NACA 2424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2424 airfoil Max thickness 24% at 29.7% chord Max camber 2% at 40% chord Max Cl/Cd 65.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e837-il) EPPLER E837 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E837 hydrofoil Max thickness 16.1% at 36.9% chord Max camber 0% at 0% chord Max Cl/Cd 65.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20606-il) NASA SC(2)-0606 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0606 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.3% at 81% chord Max Cl/Cd 65.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe703-il) GOE 703 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord Max Cl/Cd 65.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 65.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(s4096-il) S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 12.5% at 34% chord Max camber 1.2% at 34% chord Max Cl/Cd 65.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64012-il) NASA/LANGLEY 64-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 65.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca633018-il) NACA 63(3)-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 65.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf30md-il) RAF 30 MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 MOD airfoil Max thickness 7.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 65.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca001065-il) NACA 0010-65		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 65.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database