Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(dae51-il) DAE-51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord Max camber 4% at 46.4% chord Max Cl/Cd 63.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq359-il) HQ 3.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 63.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe417-il) GOE 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417 airfoil Max thickness 6% at 20% chord Max camber 6.1% at 40% chord Max Cl/Cd 63.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e214-il) E214 (11.1%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E214 low Reynolds number airfoil Max thickness 11.1% at 33.1% chord Max camber 3.7% at 56.9% chord Max Cl/Cd 63.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s803-nr) NREL's S803 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S803 tip Not recommended Max thickness 11.5% at 37.5% chord Max camber 3.7% at 46.9% chord Max Cl/Cd 63.1 at Re# 100,000 Source NWTC National WInd Technology Center

(goe233-il) GOE 233 (MVA CA4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 233 (MVA CA4) airfoil Max thickness 11.6% at 19.8% chord Max camber 8.2% at 49.8% chord Max Cl/Cd 63.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh116-il) MH 116 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 116 for a propeller for ultralight Max thickness 9.9% at 32.4% chord Max camber 4.1% at 46.4% chord Max Cl/Cd 63 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh116-il) MH 116 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 116 for a propeller for ultralight Max thickness 9.9% at 32.4% chord Max camber 4.1% at 46.4% chord Max Cl/Cd 63 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe359-il) GOE 359 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 359 airfoil Max thickness 7.8% at 30% chord Max camber 5.8% at 40% chord Max Cl/Cd 63 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s803-nr) NREL's S803 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S803 tip Not recommended Max thickness 11.5% at 37.5% chord Max camber 3.7% at 46.9% chord Max Cl/Cd 63 at Re# 100,000 Source NWTC National WInd Technology Center