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.

(nn7mk20-il) NN7 MK20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NN7 MK20 airfoil Max thickness 16.9% at 37.1% chord Max camber 3% at 59.8% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(dae51-il) DAE-51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord Max camber 4% at 46.4% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s1020-il) Ornithopter airfoil.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1020 ornithopter airfoil Max thickness 15.1% at 33.8% chord Max camber 4.6% at 57% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Max Cl/Cd 127.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(aquilasm-il) AQUILA 9.3% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AQUILA R/C sailplane airfoil Max thickness 9.4% at 31.3% chord Max camber 4% at 34.7% chord Max Cl/Cd 127.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe493-il) GOE 493 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 493 airfoil Max thickness 14.9% at 29.3% chord Max camber 3.4% at 49.3% chord Max Cl/Cd 127.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe234-il) GOE 234 (MVA CA5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 234 (MVA CA5) airfoil Max thickness 14.2% at 19.7% chord Max camber 9.2% at 49.7% chord Max Cl/Cd 127.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r1080-il) RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1080 Voyager inner aft wing airfoil Max thickness 18% at 40% chord Max camber 3.3% at 40% chord Max Cl/Cd 127 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Max Cl/Cd 127 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e558-il) EPPLER 558 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E558 general aviation airfoil Max thickness 16% at 26.4% chord Max camber 3.8% at 49.3% chord Max Cl/Cd 127 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database