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.

(goe116-il) GOE 116 (MVA MK.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord Max Cl/Cd 29.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae5213-il) RAE(NPL) 5213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5213 transonic airfoil Max thickness 10% at 35.5% chord Max camber 1.4% at 69.1% chord Max Cl/Cd 29.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiib-il) GIII BL45 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 10.4% at 39.7% chord Max camber 0.8% at 24.7% chord Max Cl/Cd 29.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 29.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe332-il) GOE 332 (PFALZ 61) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 332 (Pfalz 61) airfoil Max thickness 11.8% at 29.8% chord Max camber 6.4% at 39.8% chord Max Cl/Cd 29.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Max Cl/Cd 29.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa45m-il) USA 45 M AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45M airfoil Max thickness 11.6% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 29.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(vr5-il) BOEING-VERTOL VR-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-5 rotorcraft airfoil Max thickness 12% at 35% chord Max camber 3.4% at 35% chord Max Cl/Cd 29.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca651212a06-il) NACA 65(1)-212 a=0.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 a=0.6 airfoil Max thickness 12% at 40% chord Max camber 1.5% at 50% chord Max Cl/Cd 29.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe533-il) GOE 533 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 533 airfoil Max thickness 13.7% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 29.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database