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.

(goe677-il) GOE 677 (= M 6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 677 (= M 6) airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 81.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(amsoil1-il) RUTAN CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord Max Cl/Cd 81.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe683-il) GOE 683 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 683 airfoil Max thickness 19.9% at 30% chord Max camber 3% at 30% chord Max Cl/Cd 81.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rae5215-il) RAE 5215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5215 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.5% at 69.1% chord Max Cl/Cd 81.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s2055-il) S2055		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord Max Cl/Cd 81 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(hq1510-il) HQ 1.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 81 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(nacam6-il) NACA M6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M6 airfoil Max thickness 12% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 81 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord Max Cl/Cd 81 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe518-il) GOE 518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 518 airfoil Max thickness 18% at 29.8% chord Max camber 7.3% at 29.8% chord Max Cl/Cd 81 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(joukowsk0018-jf) Joukovsky f=0% t=18%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 18% symmetrical airfoil Max thickness 18% at 27.1% chord Max camber 0% at 0% chord Max Cl/Cd 81 at Re# 1,000,000 Source Javafoil generated