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.

(naca2418-il) NACA 2418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2418 airfoil Max thickness 18% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 8.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(b29root-il) B-29 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing B-29 root airfoil Max thickness 22% at 30.2% chord Max camber 1.7% at 30.2% chord Max Cl/Cd 8.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m8-il) NACA M8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-8 airfoil Max thickness 11.7% at 15% chord Max camber 8% at 30% chord Max Cl/Cd 8.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(strand-il) STRAND AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Strand high lift airfoil Max thickness 15.4% at 26.1% chord Max camber 4.1% at 32.1% chord Max Cl/Cd 8.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 8.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(defcnd2-il) DEFIANT CANARD BL110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL110 airfoil Max thickness 14.7% at 28.6% chord Max camber 3.8% at 28.6% chord Max Cl/Cd 8.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx72ls160-il) FX 72-LS-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 72-LS-160 airfoil Max thickness 16% at 37.1% chord Max camber 8.2% at 43.5% chord Max Cl/Cd 8.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx61147-il) FX 61-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-147 airfoil Max thickness 14.8% at 33.9% chord Max camber 3.2% at 33.9% chord Max Cl/Cd 8.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17AII-182 airfoil (as tested at NASA) Max thickness 18.8% at 35.3% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 8.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx6617a2-il) FX 66-17AII-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord Max Cl/Cd 8.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database