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.

(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Source UIUC Airfoil Coordinates Database
(marske2-il) MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IA airfoil (NACA 23112/43012A hybrid) Max thickness 12.1% at 25% chord Max camber 2.7% at 15% chord Source UIUC Airfoil Coordinates Database
(mh117-il) MH 117 9.8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 117 for a propeller for ultralight (tip) Max thickness 9.8% at 29.1% chord Max camber 2.7% at 44.6% chord Source UIUC Airfoil Coordinates Database
(mh18-il) MH 18 11.16%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 18 for F3D Pylon Racing Max thickness 11.1% at 36.8% chord Max camber 2.7% at 42.1% chord Source UIUC Airfoil Coordinates Database
(n9-il) N-9		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-9 airfoil Max thickness 8.5% at 30% chord Max camber 2.7% at 40% chord Source UIUC Airfoil Coordinates Database

(naca64a410-il) NACA 64A410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A410 airfoil Max thickness 10% at 39.9% chord Max camber 2.7% at 50% chord Source UIUC Airfoil Coordinates Database
(s2027-il) S2027		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2027 low Reynolds number airfoil Max thickness 14.5% at 29.4% chord Max camber 2.7% at 38.3% chord Source UIUC Airfoil Coordinates Database
(s4233-il) S4233-136-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord Max camber 2.7% at 48.8% chord Source UIUC Airfoil Coordinates Database
(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord Source UIUC Airfoil Coordinates Database
(ah81131-il) AH 81-131		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-131 airfoil Max thickness 13.1% at 40.2% chord Max camber 2.8% at 40.2% chord Source UIUC Airfoil Coordinates Database