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.

(mh81-il) MH 81 13%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e474-il) E474 (14.09%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E474 aerobatic aircraft airfoil Max thickness 14.1% at 21.5% chord Max camber 0% at 0% chord Max Cl/Cd 22.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sc20010-il) NASA SC(2)-0010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 22.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe29b-il) GOE 29B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 29B airfoil Max thickness 9.4% at 19.8% chord Max camber 6.5% at 29.8% chord Max Cl/Cd 22.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah93k132-il) AH 93-K-132/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-132/15 airfoil for use with flaps (K) Max thickness 13.2% at 41.2% chord Max camber 3.5% at 41.2% chord Max Cl/Cd 22.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(e426-il) EPPLER 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E426 airfoil Max thickness 10.8% at 25.5% chord Max camber 0.6% at 50.6% chord Max Cl/Cd 22.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca0006-il) NACA 0006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 22.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil Max thickness 12% at 30.9% chord Max camber 3.5% at 37.1% chord Max Cl/Cd 22.8 at Re# 50,000 Source NASA
(s8037-il) S8037 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8037 low Reynolds number airfoil Max thickness 16% at 33.5% chord Max camber 1.9% at 40.4% chord Max Cl/Cd 22.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(stcyr172-il) St. CYR 172 (Royer)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 172 (Royer) airfoil Max thickness 13.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 22.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database