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.

(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 40.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca16018-il) NACA 16-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-018 airfoil Max thickness 18% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 40.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20403-il) NASA SC(2)-0403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord Max Cl/Cd 39.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord Max Cl/Cd 36.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 36.2 at Re# 1,000,000 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 34.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe444-il) GOE 444 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 444 airfoil Max thickness 5.6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 34.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(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 33.7 at Re# 1,000,000 Source Generated
(sc20402-il) NASA SC(2)-0402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0402 airfoil (NASA TP-2969) Max thickness 2% at 34% chord Max camber 0.5% at 83% chord Max Cl/Cd 32.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 31.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database