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.

(b707d-il) BOEING 707 .54 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 40% chord Max camber 1.8% at 30% chord Max Cl/Cd 76.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa32-il) USA 32 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-32 airfoil Max thickness 14.7% at 19.8% chord Max camber 9.3% at 39.8% chord Max Cl/Cd 76.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord Max camber 2.4% at 82.5% chord Max Cl/Cd 76.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe559-il) GOE 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 559 airfoil Max thickness 11.2% at 30% chord Max camber 3.4% at 30% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx76120-il) WORTMANN FX 76-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-120 symmetrical airfoil Max thickness 12.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(fx66h60-il) FX 66-H-60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(tsagi8-il) TSAGI 8% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 8% airfoil Max thickness 8% at 30% chord Max camber 1.3% at 30% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe513-il) GOE 513 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord Max camber 5.2% at 39.8% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf26-il) RAF 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-26 airfoil Max thickness 6.6% at 29.9% chord Max camber 2.1% at 49.9% chord Max Cl/Cd 76.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database