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.

(oaf095-il) OAF095 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord Source UIUC Airfoil Coordinates Database
(oaf102-il) OAF102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF102 Fenestron airfoil Max thickness 10.2% at 28.7% chord Max camber 3.6% at 53.1% chord Source UIUC Airfoil Coordinates Database
(oaf117-il) OAF117 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord Source UIUC Airfoil Coordinates Database
(oaf128-il) OAF128 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF128 Fenestron airfoil Max thickness 12.8% at 23.2% chord Max camber 1% at 43.7% chord Source UIUC Airfoil Coordinates Database
(oaf139-il) OAF139 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF139 Fenestron airfoil Max thickness 13.7% at 23.2% chord Max camber 0% at 0.1% chord Source UIUC Airfoil Coordinates Database
(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D root (BL17.5) airfoil Max thickness 16.5% at 38.9% chord Max camber 1.3% at 68.3% chord Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Source UIUC Airfoil Coordinates Database
(p51hroot-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 15.5% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(p51htip-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database

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