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.

(nacam2-il) NACA M2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M2 airfoil Max thickness 8.1% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 44.5 at Re# 500,000 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 44.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca23024-il) NACA 23024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% chord Max Cl/Cd 44.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca16012-il) NACA 16-012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-012 airfoil Max thickness 12% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 44.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n64008a-il) NACA 64-008A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 44.5 at Re# 500,000 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 44.5 at Re# 500,000 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 44.4 at Re# 500,000 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 44.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(lwk80150k25-il) LWK 80-150/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-150/K25 symmetrical airfoil Max thickness 15% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 44 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(k2-il) GRUMMAN K-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord Max camber 1.3% at 88.3% chord Max Cl/Cd 44 at Re# 500,000 Source UIUC Airfoil Coordinates Database