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.

(naca0010-il) NACA 0010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sc20414-il) NASA SC(2)-0414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0414 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 1.5% at 83% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lg10sc-il) LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia/NASA/Blackwell rotorcraft airfoil Max thickness 10% at 32% chord Max camber 1.5% at 16% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lwk79100-il) LWK 79-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e197-il) E197 (13.49%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E197 low Reynolds number airfoil Max thickness 13.5% at 34.6% chord Max camber 2.8% at 43.7% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(naca66209-il) NACA 66-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe228-il) GOE 228 (MVA H.38) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(amsoil2-il) RUTAN WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer wing airfoil Max thickness 11.8% at 39% chord Max camber 1% at 48% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63215b-il) NACA 63(2)-215 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database