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.

(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 50.3 at Re# 200,000 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 50.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe435-il) GOE 435 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 435 airfoil Max thickness 26.1% at 27.8% chord Max camber 4.7% at 48% chord Max Cl/Cd 50.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe559-il) GOE 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 559 airfoil Max thickness 11.2% at 30% chord Max camber 3.4% at 30% chord Max Cl/Cd 50.2 at Re# 200,000 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 50.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 50.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx77w153-il) WORTMANN FX 77-W-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-153 wind turbine airfoil Max thickness 15.2% at 27.9% chord Max camber 4.5% at 27.9% chord Max Cl/Cd 50.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(k3-il) GRUMMAN K-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord Max Cl/Cd 50.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 50.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq010-il) HQ 0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 50.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database