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.

(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fxl142k-il) FX LIII-142 K 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX LIII-142 K 25 airfoil Max thickness 14.2% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa33-il) USA 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae103-il) RAE 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1221-il) S1221 w/o flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(fx74080-il) WORTMANN FX 74-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 74-080 airfoil Max thickness 8.2% at 43.5% chord Max camber 4.3% at 46.7% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa29-il) USA 29 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fxlv152-il) WORTMANN FX L V-152 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX L V-152 airfoil Max thickness 15.3% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sc1095r8-il) SIKORSKY SC1094R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Velkoff SC1095 R8 rotorcraft airfoil Max thickness 9.3% at 26.5% chord Max camber 2.1% at 20.5% chord Max Cl/Cd 27 at Re# 50,000 Source UIUC Airfoil Coordinates Database