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.

(kc135b-il) KC-135 BL124.32 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 13% at 40% chord Max camber 1.4% at 20% chord Max Cl/Cd 31.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s3016-il) S3016-095-87		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3016 low Reynolds number airfoil Max thickness 9.5% at 28.9% chord Max camber 1.8% at 43.1% chord Max Cl/Cd 31.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 31.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e184-il) E184 (8.33%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E184 low Reynolds number airfoil Max thickness 8.3% at 33.3% chord Max camber 0.8% at 38.3% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa28-il) USA 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(clarkys-il) CLARK YS AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(vr8b-il) BOEING-VERTOL VR-8 AIRFOIL WITH TAB		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil with tab Max thickness 8.2% at 35% chord Max camber 1.2% at 35% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 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 10.8% at 40% chord Max camber 1.4% at 30% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(2032c-il) 20-32C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dillner 20-32-C low Reynolds number airfoil Max thickness 8% at 20% chord Max camber 6.9% at 40% chord Max Cl/Cd 31.7 at Re# 50,000 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 Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database