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.

(raf30-il) RAF 30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 airfoil Max thickness 12.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 58.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(joukowsk0009-jf) Joukovsky f=0% t=9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 9% symmetrical airfoil Max thickness 9% at 25.5% chord Max camber 0% at 0% chord Max Cl/Cd 58.2 at Re# 500,000 Source Javafoil generated
(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 58.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n63012a-il) NACA 63012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-012A airfoil Max thickness 12% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 58.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b707c-il) BOEING 707 .40 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 9.6% at 30% chord Max camber 1.9% at 15% chord Max Cl/Cd 58.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 58 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20414-il) NASA SC(2)-0414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0414 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 1.5% at 83% chord Max Cl/Cd 57.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s9027-il) S9027 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord Max Cl/Cd 57.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca0010-il) NACA 0010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 57.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 57.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database