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.

(goe738-il) GOE 738 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 738 airfoil Max thickness 15.4% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe227-il) GOE 227 (MVA H.37) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord Max camber 7.8% at 50% chord Max Cl/Cd 23.3 at Re# 50,000 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 23.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa40-il) USA 40 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40 airfoil Max thickness 13.3% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 23.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca632a015-il) NACA 63(2)A-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord Max camber 1.7% at 14.6% chord Max Cl/Cd 23.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(n64008a-il) NACA 64-008A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 23.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx74130wp2mod-il) 74-130 WP2 MOD		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann 74-130 WP2 MOD airfoil Max thickness 12.9% at 43.5% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 23.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sc20612-il) NASA SC(2)-0612 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0612 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.9% at 81% chord Max Cl/Cd 23.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e379-il) EPPLER 379 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E379 ultralight airfoil Max thickness 2.2% at 5.8% chord Max camber 8% at 31.8% chord Max Cl/Cd 23.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 23.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database