Airfoil database search (Symmetrical)

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.

(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 28.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf27-il) RAF 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq010-il) HQ 0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 28 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae101-il) RAE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae103-il) RAE 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx79l100-il) FX 79-L-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 27.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf27-il) RAF 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae101-il) RAE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63010a-il) NACA 63A010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

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