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.

(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 65.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 65.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64015-il) NACA 642-015 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015 airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 65 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca66209-il) NACA 66-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 64.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq09-il) HQ 0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 64.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 64.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64012a-il) NACA 64-012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 64.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ht12-il) HT12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord Max Cl/Cd 64.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx69pr281-il) FX 69-PR-281		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord Max camber 5.6% at 50% chord Max Cl/Cd 64.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n63012a-il) NACA 63012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-012A airfoil Max thickness 12% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 64.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database