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.

(rae5215-il) RAE 5215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5215 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.5% at 69.1% chord Source UIUC Airfoil Coordinates Database
(s6061-il) S6061 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6061 low Reynolds number airfoil Max thickness 9% at 34% chord Max camber 1.5% at 43.6% chord Source UIUC Airfoil Coordinates Database
(mh44-il) MH 44 9.66%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 44 for flying wings Max thickness 9.6% at 27.1% chord Max camber 1.5% at 36.9% chord Source UIUC Airfoil Coordinates Database
(naca651212a06-il) NACA 65(1)-212 a=0.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 a=0.6 airfoil Max thickness 12% at 40% chord Max camber 1.5% at 50% chord Source UIUC Airfoil Coordinates Database
(n64212mb-il) NACA 64(1)-212 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Source UIUC Airfoil Coordinates Database
(hq159-il) HQ 1.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1.5% at 50% chord 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 Source UIUC Airfoil Coordinates Database
(rc10n1-il) NASA/LANGLEY RC-10(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-10(N)1 rotorcraft airfoil Max thickness 10% at 37.6% chord Max camber 1.5% at 25% chord Source UIUC Airfoil Coordinates Database
(hq158-il) HQ 1.5/8 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 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Source UIUC Airfoil Coordinates Database

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