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.

(s808-nr) NREL's S808 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord Max Cl/Cd 78.9 at Re# 500,000 Source NWTC National WInd Technology Center
(goe735-il) GOE 735 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 735 airfoil Max thickness 20.1% at 30% chord Max camber 4.4% at 30% chord Max Cl/Cd 78.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf15-il) RAF 15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-15 airfoil Max thickness 6.5% at 15% chord Max camber 2.6% at 30% chord Max Cl/Cd 78.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiih-il) GIII BL207 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 78.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(pt40-il) PT40		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord Max Cl/Cd 78.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe286-il) GOE 286 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 286 airfoil Max thickness 9.4% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 78.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca643218-il) NACA 64(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 78.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(giiig-il) GIII BL167 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 78.8 at Re# 500,000 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 78.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx69h083-il) BELL/WORTMANN FX 69-H-083 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-083 rotorcraft airfoil Max thickness 8.4% at 33.3% chord Max camber 2.5% at 33.3% chord Max Cl/Cd 78.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database