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.

(raf27-il) RAF 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 71.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(avistar-il) AVISTAR		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord Max Cl/Cd 71.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20503-il) NASA SC(2)-0503 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0503 airfoil (NASA TP-2969) Max thickness 3% at 32% chord Max camber 0.8% at 82% chord Max Cl/Cd 71.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(eh2510-il) EH 2.5/10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.5/10 for tailless R/C aircraft Max thickness 10% at 30% chord Max camber 2.5% at 25% chord Max Cl/Cd 71.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca671215-il) NACA 67		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Max Cl/Cd 71.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 71.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx77080-il) WORTMANN FX 77-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-080 symmetrical airfoil Max thickness 8% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 71.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(r140sm-il) R140 12.04% (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord Max camber 0.4% at 39.3% chord Max Cl/Cd 71.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(du8608418-il) DU86-084/18 8.44%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord Max Cl/Cd 71 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca0021-il) NACA 0021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0021 airfoil Max thickness 21% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 71 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database