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.

(goe445-il) GOE 445 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 445 airfoil Max thickness 6.4% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(hq07-il) HQ 0/7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s9033-il) S9033 (7.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(raf30md-il) RAF 30 MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-30 MOD airfoil Max thickness 7.6% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(fx77080-il) WORTMANN FX 77-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-080 symmetrical airfoil Max thickness 8% at 27.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s9027-il) S9027 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca0008-il) NACA 0008		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord 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 Source UIUC Airfoil Coordinates Database
(m2-il) NACA M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-2 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

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