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.

(coanda2-il) Coanda 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 2 airfoil Max thickness 6% at 30% chord Max camber 2.9% at 30% chord Max Cl/Cd 49.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx76120-il) WORTMANN FX 76-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-120 symmetrical airfoil Max thickness 12.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 49.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 49.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe15k-il) GOE 15K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 15K airfoil Max thickness 15% at 50% chord Max camber 3.4% at 50% chord Max Cl/Cd 49.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 49.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(n13-il) N-13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord Max Cl/Cd 49.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx84w218-il) FX 84-W-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-218 airfoil for use on wind turbines (W) Max thickness 22% at 33.9% chord Max camber 3.2% at 43.5% chord Max Cl/Cd 49.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag47c03-il) AG47c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47c -03f airfoil Max thickness 5.1% at 22.4% chord Max camber 1.3% at 33.4% chord Max Cl/Cd 49.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr15-il) BOEING-VERTOL VR-15 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-15 transonic rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.3% at 20% chord Max Cl/Cd 49.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx76120-il) WORTMANN FX 76-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-120 symmetrical airfoil Max thickness 12.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 49.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database