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.

(ui1720-il) UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois UI-1720 high lift airfoil Max thickness 13.8% at 19% chord Max camber 4.6% at 21.2% chord Max Cl/Cd 78 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca63209-il) NACA 63-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 78 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 78 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe113-il) GOE 113 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 113 airfoil Max thickness 6.7% at 30% chord Max camber 3% at 40% chord Max Cl/Cd 78 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh64-il) MH 64 8.59%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord Max Cl/Cd 78 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(eh3012-il) EH 3.0/12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 3.0/12 for tailless R/C aircraft Max thickness 12% at 30% chord Max camber 2.9% at 25% chord Max Cl/Cd 77.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(b29root-il) B-29 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing B-29 root airfoil Max thickness 22% at 30.2% chord Max camber 1.7% at 30.2% chord Max Cl/Cd 77.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca23112-jf) NACA 23112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 23112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 1.2% at 14.7% chord Max Cl/Cd 77.9 at Re# 500,000 Source Javafoil generated
(mh26-il) MH 26 10.99%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 26 for F3D Pylon Racing (extended laminar flow) Max thickness 11% at 42.3% chord Max camber 1.4% at 42.3% chord Max Cl/Cd 77.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ag11-il) AG11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG11 airfoil Max thickness 5.8% at 26% chord Max camber 2.2% at 29.7% chord Max Cl/Cd 77.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database