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.

(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 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m685-il) M6 (85%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (85%) Max thickness 10.2% at 30% chord Max camber 1.9% at 30% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq1511-il) HQ 1.5/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 1.5% at 50% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe490-il) GOE 490 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 490 airfoil Max thickness 8.8% at 19.9% chord Max camber 3.8% at 39.9% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e417-il) EPPLER 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E417 general purpose airfoil Max thickness 14.2% at 38.3% chord Max camber 3.1% at 76.3% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(vr8-il) BOEING-VERTOL VR-8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil Max thickness 8.2% at 35% chord Max camber 1.3% at 35% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh23-il) MH 23 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 23 for F3D Pylon Racing (extended laminar flow) Max thickness 8% at 37.5% chord Max camber 1.2% at 42.7% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fg2-il) Fage & Collins 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 2 airfoil Max thickness 8.2% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd6060-il) SD6060-104-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD6060 low Reynolds number airfoil Max thickness 10.4% at 33.9% chord Max camber 1.6% at 38.6% chord Max Cl/Cd 33.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq109-il) HQ 1.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 33.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database