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.

(e479-il) EPPLER 479 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E479 aerobatic aircraft airfoil Max thickness 16.6% at 25.7% chord Max camber 0% at 0% chord Max Cl/Cd 88.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s2050-il) S2050 8.93%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord Max Cl/Cd 88.5 at Re# 1,000,000 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 88.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh45-il) MH 45 9.85%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 88.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord Max Cl/Cd 88.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(ag16-il) AG16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG16 airfoil Max thickness 7.1% at 23.4% chord Max camber 1.9% at 46.9% chord Max Cl/Cd 88.4 at Re# 1,000,000 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 88.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hor07-il) ONERA HOR07 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 7.2% at 23.2% chord Max camber 4.5% at 39.6% chord Max Cl/Cd 88.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s835-nr) NREL's S835 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord Max camber 2.4% at 78% chord Max Cl/Cd 88.4 at Re# 1,000,000 Source NWTC National WInd Technology Center
(bacnlf-il) BOEING HSNLF AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord Max Cl/Cd 88.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database