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.

(goe449-il) GOE 449 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 449 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 34.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s9026-il) S9026 (9.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane Max thickness 9.5% at 27.3% chord Max camber 0% at 0% chord Max Cl/Cd 34.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m3-il) NACA M3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 34.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nacam3-il) NACA M3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 34.6 at Re# 100,000 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 34.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e858-il) EPPLER 858 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord Max Cl/Cd 34.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah82150f-il) AH 82-150 F		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 F airfoil Max thickness 15% at 43.5% chord Max camber 3.6% at 46.7% chord Max Cl/Cd 34.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca0008-il) NACA 0008		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 34.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e836-il) EPPLER E836 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E836 hydrofoil Max thickness 12.6% at 42.8% chord Max camber 0% at 0% chord Max Cl/Cd 34.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca64a010-il) NACA 64A-010 10.0%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A010 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 34.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database