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.

(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe423-il) GOE 423 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(raf25-il) RAF 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca63a210-il) NACA 63A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae5212-il) RAE(NPL) 5212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord Max camber 1.8% at 69.1% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe217-il) GOE 217 (MVA MK.12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 217 (MVA MK.12) airfoil Max thickness 19% at 29.2% chord Max camber 6.3% at 59.4% chord Max Cl/Cd 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord Max Cl/Cd 40.2 at Re# 100,000 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 40.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(vr13-il) BOEING-VERTOL VR-13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-13 rotorcraft airfoil Max thickness 9.5% at 35% chord Max camber 2% at 20% chord Max Cl/Cd 40.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(npl9627-il) NPL 9627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord Max camber 0.9% at 40.4% chord Max Cl/Cd 40.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database