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.

(clarkys-il) CLARK YS AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord Max Cl/Cd 47 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag12-il) AG12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG12 airfoil Max thickness 6.2% at 20.8% chord Max camber 1.8% at 42.8% chord Max Cl/Cd 47 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe527-il) GOE 527 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 527 airfoil Max thickness 16.5% at 29.5% chord Max camber 5.8% at 39.5% chord Max Cl/Cd 47 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord Max camber 1.3% at 50% chord Max Cl/Cd 47 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(vr1-il) BOEING-VERTOL VR-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-1 rotorcraft airfoil Max thickness 11% at 35.3% chord Max camber 1.5% at 43.3% chord Max Cl/Cd 46.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(oaf117-il) OAF117 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord Max Cl/Cd 46.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(du8608418-il) DU86-084/18 8.44%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord Max Cl/Cd 46.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx38153-il) FX 38-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord Max Cl/Cd 46.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(tempest3-il) HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 96.77% semispan airfoil (NPL?) Max thickness 10% at 38.7% chord Max camber 1% at 40.7% chord Max Cl/Cd 46.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe426-il) GOE 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 426 airfoil Max thickness 13.6% at 30% chord Max camber 4.6% at 40% chord Max Cl/Cd 46.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database