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.

(fx08s176-il) WORTMANN FX 08-S-176 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 08-S-176 airfoil Max thickness 17.6% at 37.1% chord Max camber 5.7% at 37.1% chord Max Cl/Cd 9.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe562-il) GOE 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 9.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx72150b-il) WORTMANN FX 72-MS-150B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 72-MS-150B airfoil Max thickness 15% at 37.1% chord Max camber 9.7% at 46.7% chord Max Cl/Cd 9.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe528-il) GOE 528 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 528 airfoil Max thickness 12.5% at 29.8% chord Max camber 6.2% at 39.8% chord Max Cl/Cd 9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s815-nr) NREL's S815 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord Max Cl/Cd 9 at Re# 50,000 Source NWTC National WInd Technology Center

(e546-il) EPPLER 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% chord Max Cl/Cd 8.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Max Cl/Cd 8.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(geminism-il) GEMINI (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord Max Cl/Cd 8.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe462-il) GOE 462 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 462 airfoil Max thickness 11% at 9.9% chord Max camber 13.4% at 29.9% chord Max Cl/Cd 8.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Max Cl/Cd 8.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database