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.

(glennmartin2-il) Glenn Martin 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord Max Cl/Cd 101.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(v43012-il) BOEING VERTOL V43012-1.58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V43012-1.58 rotorcraft airfoil Max thickness 12% at 32% chord Max camber 3.7% at 15% chord Max Cl/Cd 101.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe701-il) GOE 701 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 701 airfoil Max thickness 12.5% at 29.6% chord Max camber 4.9% at 39.6% chord Max Cl/Cd 101.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e473-il) EPPLER 473 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E473 aerobatic aircraft airfoil Max thickness 16.2% at 21.2% chord Max camber 0% at 0% chord Max Cl/Cd 101.3 at Re# 1,000,000 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 101.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(sa7035-il) SA7035		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7035 Max thickness 9.2% at 27.9% chord Max camber 2.4% at 41.9% chord Max Cl/Cd 101.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx84w218-il) FX 84-W-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-218 airfoil for use on wind turbines (W) Max thickness 22% at 33.9% chord Max camber 3.2% at 43.5% chord Max Cl/Cd 101.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3011-il) HQ 3.0/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 101.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe309-il) GOE 309 (MVA H.41) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 309 (MVA H.41) airfoil Max thickness 8.4% at 30% chord Max camber 4.7% at 30% chord Max Cl/Cd 101.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s818-nr) NREL's S818 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord Max Cl/Cd 101.1 at Re# 1,000,000 Source NWTC National WInd Technology Center