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.

(clarkys-il) CLARK YS AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s4094-il) S4094 (root airfoil designed for and used on 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 9.9% at 29.1% chord Max camber 1.8% at 33.6% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e326-il) EPPLER 326 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E326 flying wing airfoil Max thickness 12.9% at 33.4% chord Max camber 2.1% at 19.5% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ames01-il) NASA/AMES A-01 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m5-il) NACA M5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord Max camber 2.1% at 30.1% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(n64212mb-il) NACA 64(1)-212 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s3-il) REPUBLIC S-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 76.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 76.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca663218-il) NACA 66(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 76.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 76.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database