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.

(goe228-il) GOE 228 (MVA H.38) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% chord Max Cl/Cd 88.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe702-il) GOE 702 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 702 airfoil Max thickness 16.6% at 19.4% chord Max camber 5.1% at 39.4% chord Max Cl/Cd 88.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe363-il) GOE 363 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 363 airfoil Max thickness 11.1% at 19.8% chord Max camber 5.7% at 39.8% chord Max Cl/Cd 88.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe100-il) GOE 100 (SOPWITH) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 100 (Sopwith) airfoil Max thickness 6.6% at 20% chord Max camber 3.6% at 39.9% chord Max Cl/Cd 88.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 88.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe54-il) GOE 54 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 54 airfoil Max thickness 6.5% at 14.9% chord Max camber 3.5% at 19.9% chord Max Cl/Cd 88.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Max Cl/Cd 88.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh150-il) MH 150 23.89%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 150 for marine ruddershaft for torque reduction (schottel units) Max thickness 23.9% at 27.2% chord Max camber 4.5% at 53.8% chord Max Cl/Cd 88.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e635-il) EPPLER 635 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E635 airfoil Max thickness 11.6% at 26.2% chord Max camber 2.9% at 22.2% chord Max Cl/Cd 88 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e502-il) EPPLER 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E502 general purpose airfoil Max thickness 15.6% at 42.1% chord Max camber 1.5% at 32.3% chord Max Cl/Cd 88 at Re# 500,000 Source UIUC Airfoil Coordinates Database