Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(e226-il) E226 (10.19%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E226 low Reynolds number airfoil Max thickness 10.2% at 31.3% chord Max camber 0.5% at 56.9% chord Max Cl/Cd 55.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ames01-il) NASA/AMES A-01 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-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 55.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca662415-il) NACA 66(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord Max Cl/Cd 55.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s833-nr) NREL's S833 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord Max Cl/Cd 55.3 at Re# 200,000 Source NWTC National WInd Technology Center
(oa209-il) ONERA OA209 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord Max camber 1.6% at 17.1% chord Max Cl/Cd 55.3 at Re# 200,000 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 55.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e1212-il) EPPLER E1212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1212 general aviation airfoil Max thickness 17.7% at 23.4% chord Max camber 3.2% at 36.4% chord Max Cl/Cd 55.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s8064-il) S8064		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord Max camber 1.1% at 56.2% chord Max Cl/Cd 55.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e485-il) EPPLER 485 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E485 tailplane airfoil Max thickness 12.5% at 31.8% chord Max camber 1.1% at 27.1% chord Max Cl/Cd 55.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(bacxxx-il) BOEING BACXXX AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 55.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database