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.

(mh20-il) MH 20 9.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 20 for F3D Pylon Racing Max thickness 9% at 32.2% chord Max camber 1.9% at 37.3% chord Source UIUC Airfoil Coordinates Database
(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Source UIUC Airfoil Coordinates Database
(kc135d-il) KC-135 BL351.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 9% at 40% chord Max camber 1.9% at 30% chord Source UIUC Airfoil Coordinates Database
(s8037-il) S8037 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8037 low Reynolds number airfoil Max thickness 16% at 33.5% chord Max camber 1.9% at 40.4% chord Source UIUC Airfoil Coordinates Database
(s3-il) REPUBLIC S-3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database

(ys915-il) YS-915		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	YS915 hydrofoil (Shen / Eppler) Max thickness 9.1% at 36.1% chord Max camber 1.8% at 65.6% chord Source UIUC Airfoil Coordinates Database
(pw98mod-pw) PW98-mod		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.4% at 27.5% chord Max camber 1.8% at 27.5% chord Source RC Groups
(ag45ct02r-il) AG45ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord Source UIUC Airfoil Coordinates Database
(rg12a189-il) RG 12A-1.8/9.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12A-1.8/9.0 airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord Source UIUC Airfoil Coordinates Database
(rg12a-il) AIRFOIL PROFILE12A 9.00%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12A airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord Source UIUC Airfoil Coordinates Database