Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(as5048-il) AS5048 (18%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil Max thickness 18% at 38.3% chord Max camber 0.8% at 77.8% chord Source UIUC Airfoil Coordinates Database
(oa206-il) ONERA OA206 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA206 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 6% at 31.8% chord Max camber 0.8% at 19.6% chord Source UIUC Airfoil Coordinates Database
(s8066-il) S8066 (10% version of S8065 w/ lower surface aerodynamically similar)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-40 pylon racing (10%). Max thickness 10% at 37.7% chord Max camber 0.8% at 56.3% chord Source UIUC Airfoil Coordinates Database
(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord Max camber 0.9% at 20.2% chord Source UIUC Airfoil Coordinates Database
(mh106-il) MH 106 13.07%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 106 for stall controlled wind turbines Max thickness 13.1% at 27.4% chord Max camber 0.9% at 27.4% chord Source UIUC Airfoil Coordinates Database

(e874-il) EPPLER 874 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E874 hydrofoil Max thickness 7.9% at 28.8% chord Max camber 0.9% at 35.7% chord Source UIUC Airfoil Coordinates Database
(dga1182-il) D.G.A. 1182		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	D.G.A. 1182 airfoil Max thickness 7.6% at 30% chord Max camber 0.9% at 20% chord Source UIUC Airfoil Coordinates Database
(tempest2-il) HAWKER TEMPEST 61% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 61% semispan airfoil (NPL?) Max thickness 12% at 37.3% chord Max camber 0.9% at 39.3% chord Source UIUC Airfoil Coordinates Database
(giiic-il) GIII BL75 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 9.9% at 39.8% chord Max camber 0.9% at 29.8% chord Source UIUC Airfoil Coordinates Database
(supermarine371ii-il) Supermarine 371-II (tip)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-II tip airfoil Max thickness 8.4% at 50% chord Max camber 0.9% at 45% chord Source UIUC Airfoil Coordinates Database