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.

(ames03-il) NASA/AMES A-03 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae5214-il) RAE 5214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n14-il) N-14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001234-il) NACA 0012-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-34 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e328-il) EPPLER 328 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E328 flying wing airfoil Max thickness 13.3% at 31.5% chord Max camber 3% at 22.1% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(n64012a-il) NACA 64-012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe802a-il) GOE 802 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 A airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(pw1211-pw) PW1211		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 7% at 24% chord Max camber 1.7% at 28.2% chord Max Cl/Cd 27.5 at Re# 50,000 Source RC Groups
(cp-100-050-gn) Cambered plate C=10% T=5% R=1.3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=10% Wall thickness=5% Radius=1.3 Max thickness 7% at 4.2% chord Max camber 7.9% at 46.5% chord Max Cl/Cd 27.5 at Re# 50,000 Source Generated
(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 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database