Airfoil Tools
Search 1638 airfoils

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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.

(cp-160-050-gn) Cambered plate C=16% T=5% R=0.86		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=16% Wall thickness=5% Radius=0.861 Max thickness 5.2% at 3.4% chord Max camber 14.3% at 49.2% chord Max Cl/Cd 34.2 at Re# 200,000 Source Generated
(fx77w270s-il) FX 77-W-270S		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-270S airfoil for use on wind turbines (W) Max thickness 27.1% at 33.9% chord Max camber 4.2% at 27.9% chord Max Cl/Cd 34.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx2-il) WORTMANN FX 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord Max Cl/Cd 34.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr9-il) BOEING-VERTOL VR-9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-9 rotorcraft airfoil Max thickness 6.1% at 35% chord Max camber 0.3% at 35% chord Max Cl/Cd 34.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ht08-il) HT08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT08 airfoil Max thickness 5% at 20.2% chord Max camber 0% at 0% chord Max Cl/Cd 34.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx2-il) WORTMANN FX 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord Max Cl/Cd 34.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n5h20-il) NACA 5-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 34.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe571-il) GOE 571 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 571 airfoil Max thickness 24.9% at 29.4% chord Max camber 9.8% at 29.4% chord Max Cl/Cd 34 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe443-il) GOE 443 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 443 airfoil Max thickness 5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 34 at Re# 200,000 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 34 at Re# 200,000 Source UIUC Airfoil Coordinates Database