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.

(goe121-il) GOE 121 (MVA H.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 121 (MVA H.1) airfoil Max thickness 6.7% at 19.9% chord Max camber 4.6% at 39.9% chord Max Cl/Cd 97.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca2411-il) NACA 2.5411		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2411 airfoil Max thickness 11% at 29.5% chord Max camber 2.5% at 39.6% chord Max Cl/Cd 97.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(eh2012-il) EH 2.0/12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 97.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe397-il) GOE 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 397 airfoil Max thickness 5.1% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 97.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe676-il) GOE 676 (= M 12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 97.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 97.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e540-il) EPPLER 540 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E540 general aviation airfoil Max thickness 16.9% at 45.5% chord Max camber 1.6% at 35.7% chord Max Cl/Cd 97.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(clarkyh-il) CLARK YH AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YH airfoil Max thickness 11.9% at 30% chord Max camber 2.5% at 30% chord Max Cl/Cd 97.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag45c03-il) AG45c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45c -03f airfoil Max thickness 6.9% at 23.5% chord Max camber 2% at 31.7% chord Max Cl/Cd 97.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Max Cl/Cd 97.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database