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.

(naca633018-il) NACA 63(3)-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 61.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah93w300-il) AH 93-W-300		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-300 airfoil for use on wind turbines (W) Max thickness 30% at 27.9% chord Max camber 1.6% at 72.1% chord Max Cl/Cd 61.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx76100-il) WORTMANN FX 76-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 61.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Max Cl/Cd 61.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e837-il) EPPLER E837 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E837 hydrofoil Max thickness 16.1% at 36.9% chord Max camber 0% at 0% chord Max Cl/Cd 61.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(hor04-il) ONERA HOR04 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord Max Cl/Cd 61.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e228-il) E10(08%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E228 low Reynolds number airfoil Max thickness 10.1% at 31.9% chord Max camber 0.3% at 31.9% chord Max Cl/Cd 61.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord Max Cl/Cd 61.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 61.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(rc1264c-il) NASA/LANGLEY RC12-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 12-64C rotorcraft airfoil Max thickness 12% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 61.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database