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.

(s4110-il) S4110		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord Max Cl/Cd 60.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe372-il) GOE 372 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 372 airfoil Max thickness 6.2% at 29.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 60.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(cootie-il) WACO COOTIE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Waco Cootie airfoil Max thickness 8.5% at 30% chord Max camber 5.5% at 40% chord Max Cl/Cd 60.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq3010-il) HQ 3.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 60 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe529-il) GOE 529 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 529 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.8% at 39.9% chord Max Cl/Cd 60 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(s826-nr) NREL's S826 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef Max thickness 14% at 33.7% chord Max camber 4.3% at 62% chord Max Cl/Cd 60 at Re# 100,000 Source NWTC National WInd Technology Center
(goe419-il) GOE 419 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 419 airfoil Max thickness 5.3% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 60 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe380-il) GOE 380 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 380 airfoil Max thickness 6.6% at 30% chord Max camber 5.6% at 30% chord Max Cl/Cd 60 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe402-il) GOE 402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 402 airfoil Max thickness 6.8% at 20% chord Max camber 5.7% at 30% chord Max Cl/Cd 59.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq309-il) HQ 3.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 59.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database