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.

(goe14-il) GOE 14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 14 airfoil Max thickness 9.9% at 29.8% chord Max camber 6.9% at 29.8% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe275-il) GOE 275 (DAIMLER VI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 275 (DAIMLER VI) airfoil Max thickness 7.7% at 19.9% chord Max camber 4.7% at 29.9% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe566-il) GOE 566 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 566 airfoil Max thickness 8.7% at 30% chord Max camber 2.6% at 40% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe344-il) GOE 344 (PFALZ 71) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh25-il) MH 25 9.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow) Max thickness 10% at 42.2% chord Max camber 1.4% at 42.2% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe316-il) GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 316 (Hansa-Brandenburg IV.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq1511-il) HQ 1.5/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 1.5% at 50% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s826-nr) NREL's S826 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef Max thickness 14% at 33.7% chord Max camber 4.3% at 62% chord Max Cl/Cd 34.4 at Re# 50,000 Source NWTC National WInd Technology Center
(goe591-il) GOE 591 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 591 airfoil Max thickness 11.2% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s3024-il) AIRFOIL 3024 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord Max Cl/Cd 34.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database