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.

(ag17-il) AG17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG17 airfoil Max thickness 6.5% at 22.1% chord Max camber 2% at 45.5% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca4415-il) NACA 4415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq1511-il) HQ 1.5/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 1.5% at 50% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe320-il) GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 320 (Hansa-Brandenburg II.1) airfoil Max thickness 12.3% at 29.8% chord Max camber 6.2% at 29.8% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s6062-il) S6062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(fx61168-il) FX 61-168 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord Max camber 3% at 37.1% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq1512-il) HQ 1.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag16-il) AG16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG16 airfoil Max thickness 7.1% at 23.4% chord Max camber 1.9% at 46.9% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq1585-il) HQ 1.5/8.5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/8.5 R/C sailplane airfoil Max thickness 8.6% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag38-il) AG38		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG38 airfoil Max thickness 7% at 27.7% chord Max camber 2% at 36.7% chord Max Cl/Cd 48.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database