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.

(n14-il) N-14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord Max Cl/Cd 56.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe571-il) GOE 571 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 571 airfoil Max thickness 24.9% at 29.4% chord Max camber 9.8% at 29.4% chord Max Cl/Cd 56.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e297-il) EPPLER 297 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E297 tailplane airfoil Max thickness 11.4% at 37.7% chord Max camber 0% at 0% chord Max Cl/Cd 56 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca641112-il) NACA 64(1)-112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-112 airfoil Max thickness 12% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 56 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n0009sm-il) NACA-0009 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 55.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(n63210-il) NACA 63-210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Max Cl/Cd 55.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20706-il) NASA SC(2)-0706 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0706 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.6% at 82% chord Max Cl/Cd 55.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(c5a-il) LOCKHEED C-5A BL0 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 13.1% at 40% chord Max camber 0.7% at 85% chord Max Cl/Cd 55.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf25-il) RAF 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord Max Cl/Cd 55.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Max Cl/Cd 55.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database