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.

(ah21-9-il) AH21 9% version (Andrew Hollom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe336-il) GOE 336 (MVA H.44) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 336 (MVA H.44) airfoil Max thickness 9% at 29.9% chord Max camber 5.4% at 29.9% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd7090-il) SD7090 (10%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7090 low Reynolds number airfoil Max thickness 10% at 29.3% chord Max camber 1.5% at 43.6% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag38-il) AG38		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG38 airfoil Max thickness 7% at 27.7% chord Max camber 2% at 36.7% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m7-il) NACA M7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-7 airfoil Max thickness 6.2% at 40% chord Max camber 4.9% at 30% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe599-il) GOE 599 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 599 airfoil Max thickness 10% at 29.6% chord Max camber 1.5% at 59.7% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh24-il) MH 24 9.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 24 for F3D Pylon Racing (extended laminar flow) Max thickness 9% at 37.3% chord Max camber 1.2% at 37.3% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag13-il) AG13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG13 airfoil Max thickness 5.8% at 21.3% chord Max camber 2% at 41.8% chord Max Cl/Cd 34.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e374-il) E374		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E374 low Reynolds number airfoil Max thickness 10.9% at 34.3% chord Max camber 2% at 38.9% chord Max Cl/Cd 34.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe365-il) GOE 365 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 34.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database