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.

(goe595-il) GOE 595 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 595 airfoil Max thickness 9.6% at 30% chord Max camber 3% at 40% chord Source UIUC Airfoil Coordinates Database
(hq3013-il) HQ 3.0/13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(mh70-il) MH 70 11.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord Max camber 3% at 39.6% chord Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Source UIUC Airfoil Coordinates Database
(hq3012-il) HQ 3.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(waspsm-il) WASP (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord Source UIUC Airfoil Coordinates Database
(goe488-il) GOE 488 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 488 airfoil Max thickness 6.8% at 19.9% chord Max camber 3% at 39.9% chord Source UIUC Airfoil Coordinates Database
(hq3011-il) HQ 3.0/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(hq3010-il) HQ 3.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(ah88k136-il) AH 88-K-136/16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord Source UIUC Airfoil Coordinates Database

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