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.

(hq1510-il) HQ 1.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe298-il) GOE 298 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 298 airfoil Max thickness 12.8% at 19.6% chord Max camber 4.5% at 39.6% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s2055-il) S2055		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag12-il) AG12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG12 airfoil Max thickness 6.2% at 20.8% chord Max camber 1.8% at 42.8% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord Max camber 4.6% at 30% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(s4158-il) S4158		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4158 low Reynolds number airfoil Max thickness 10.9% at 35.3% chord Max camber 3.7% at 44.7% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sg6041-il) SG6041		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6041 wind turbine airfoil (high L/D) Max thickness 10% at 34.9% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rg15a111-il) RG 15A-1.8/11.0 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-1.8/11.0 airfoil Max thickness 11% at 30.2% chord Max camber 1.8% at 39.7% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Max Cl/Cd 35.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(boe103-il) BOEING 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 103 airfoil Max thickness 12.7% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 35 at Re# 50,000 Source UIUC Airfoil Coordinates Database