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.

(rg15a213-il) RG 15A 2.5/13.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 15A 2.5/13.0 airfoil Max thickness 13% at 30.2% chord Max camber 2.5% at 39.7% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(b29tip-il) B-29 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing B-29 tip airfoil Max thickness 9% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 66.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Max Cl/Cd 66.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(daytonwright6-il) Dayton-Wright 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 66.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s830-nr) NREL's S830 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef Max thickness 21% at 38.4% chord Max camber 4.4% at 70.5% chord Max Cl/Cd 66.3 at Re# 200,000 Source NWTC National WInd Technology Center

(fx73cl2152-il) FX 73-CL2-152		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rhodesg30-il) Rhode St. Genese 30		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 30 airfoil Max thickness 9.7% at 30% chord Max camber 3.2% at 40% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe645-il) GOE 645 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 645 airfoil Max thickness 15.4% at 19.4% chord Max camber 4.8% at 39.4% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(nacam12-il) NACA M12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(lds2-il) LDS-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord Max Cl/Cd 66.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database