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.

(oaf139-il) OAF139 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF139 Fenestron airfoil Max thickness 13.7% at 23.2% chord Max camber 0% at 0.1% chord Max Cl/Cd 31.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20606-il) NASA SC(2)-0606 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0606 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.3% at 81% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca001064-il) NACA 0010-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ames02-il) NASA/AMES A-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-02 transonic rotorcraft airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20614-il) NASA SC(2)-0614 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0614 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 2.1% at 81% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(sc20610-il) NASA SC(2)-0610 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0610 airfoil (NASA TP-2969) Max thickness 10% at 38% chord Max camber 1.8% at 82% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(a63a108c-il) NASA/AMES 63A108 MOD C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES modification of the NACA 63A-108 airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dh4009sm-il) dh4009sm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft Max thickness 8.9% at 41.6% chord Max camber 0.2% at 9.6% chord Max Cl/Cd 31.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca66-018-il) NACA 66-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 31.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell AH-1 rotor blade airfoil (operational loads survey) Max thickness 9.7% at 22.1% chord Max camber 0% at 0% chord Max Cl/Cd 31.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database