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.

(ag455ct02r-il) AG455ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG455ct -02f airfoil Max thickness 6.5% at 23.3% chord Max camber 1.8% at 33.1% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe418-il) GOE 418 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 418 airfoil Max thickness 12.7% at 20% chord Max camber 5.1% at 40% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rc12n1-il) NASA/LANGLEY RC-12(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(N)1 rotorcraft airfoil Max thickness 12% at 37.4% chord Max camber 1.4% at 30% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq159-il) HQ 1.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq2512-il) HQ 2.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(marske5-il) MARSKE MONARCH AIRFOIL (NACA 43012A)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Monarch airfoil (NACA 43012A) Max thickness 12.2% at 20% chord Max camber 3.4% at 15% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe198-il) GOE 198 (L.F.G. 5294) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 198 (L.F.G. 5294) airfoil Max thickness 7.8% at 19.9% chord Max camber 6.5% at 39.9% chord Max Cl/Cd 92.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(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 92.8 at Re# 1,000,000 Source NWTC National WInd Technology Center
(goe257-il) GOE 257 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 257 airfoil Max thickness 8.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 92.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rg8-il) RG 8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 8 airfoil Max thickness 10.8% at 31.1% chord Max camber 2.2% at 60.5% chord Max Cl/Cd 92.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database