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.

(goe223-il) GOE 223 (MVA H.34) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 223 (MVA H.34) airfoil Max thickness 18.8% at 29.1% chord Max camber 5.7% at 49.1% chord Max Cl/Cd 80.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah93w300-il) AH 93-W-300		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-300 airfoil for use on wind turbines (W) Max thickness 30% at 27.9% chord Max camber 1.6% at 72.1% chord Max Cl/Cd 80.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 80.3 at Re# 1,000,000 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 80.3 at Re# 1,000,000 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 80.3 at Re# 1,000,000 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 80.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe416a-il) GOE 416A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord Max Cl/Cd 80.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20712-il) NASA SC(2)-0712 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0712 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 2.2% at 81% chord Max Cl/Cd 80.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq159b-il) HQ 1.5/9 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 B R/C sailplane airfoil Max thickness 9% at 37.1% chord Max camber 1.5% at 50% chord Max Cl/Cd 80.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe16k-il) GOE 16K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 16K airfoil Max thickness 18.2% at 50% chord Max camber 4.1% at 50% chord Max Cl/Cd 80.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database