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.

(goe593-il) GOE 593 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 593 airfoil Max thickness 11.9% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 107.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag24-il) AG24 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG24 airfoil used on the Bubble Dancer R/C DLG Max thickness 8.4% at 26% chord Max camber 2.2% at 46.9% chord Max Cl/Cd 107.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe284-il) GOE 284 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 284 airfoil Max thickness 17.7% at 29.3% chord Max camber 5.1% at 39.3% chord Max Cl/Cd 107.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe276-il) GOE 276 (DAIMLER VII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 276 (DAIMLER VII) airfoil Max thickness 7.3% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 107.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 107 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(s828-nr) NREL's S828 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S828 tip 16.0% Dia=40 to 50 m Re=3.0E+6 Clmax(S)=0.90 Clmax(R)=0.89 Restrained max lift coef Max thickness 16% at 47.1% chord Max camber 2.2% at 47.1% chord Max Cl/Cd 107 at Re# 1,000,000 Source NWTC National WInd Technology Center
(naca633418-il) NACA 63		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 106.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3510-il) HQ 3.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 106.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh104-il) MH 104 15.28%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord Max Cl/Cd 106.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 106.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database