Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(naca654421a05-il) NACA 65(4)-421 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 a=0.5 airfoil Max thickness 21% at 39.9% chord Max camber 3% at 45% chord Max Cl/Cd 31.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx3-il) WORTMANN FX 3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord Max Cl/Cd 31.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11		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=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord Max Cl/Cd 31.4 at Re# 200,000 Source Generated
(fx71089a-il) WORTMANN FX 71-089A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-089A airfoil Max thickness 8.9% at 22.2% chord Max camber 0% at 0% chord Max Cl/Cd 31.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx73170a-il) WORTMANN FX 73-170 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-170 A airfoil Max thickness 17.1% at 43.5% chord Max camber 5.6% at 43.5% chord Max Cl/Cd 31.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(n1h15-il) NACA 1-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 5.5% at 40% chord Max Cl/Cd 31.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ht05-il) HT05		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT05 airfoil Max thickness 4.8% at 17.1% chord Max camber 0% at 63.3% chord Max Cl/Cd 31.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(bacj-il) BOEING AIRFOIL J (no closed TE)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord Max camber 1.7% at 78% chord Max Cl/Cd 31.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(dbln526-il) SIKORSKY DBLN-526 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky DBLN-526 double ended rotorcraft airfoil Max thickness 26% at 50% chord Max camber 4% at 50% chord Max Cl/Cd 31 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hs1430-il) HAM-STD HS1-430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 30% at 34% chord Max camber 3% at 44% chord Max Cl/Cd 31 at Re# 200,000 Source UIUC Airfoil Coordinates Database