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.

(k3311-il) K3311 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Leon Kincaid K3311 airfoil (original) Max thickness 11% at 30% chord Max camber 3.3% at 40% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq3013-il) HQ 3.0/13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe278-il) GOE 278 (DAIMLER IX) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 278 (DAIMLER IX) airfoil Max thickness 7.4% at 29.9% chord Max camber 4.3% at 29.9% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe801-il) GOE 801 (MVA 301) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 801 (MVA 301) airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe802-il) GOE 802 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(spicasm-il) SPICA 11.73% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Anderson SPICA R/C sailplane airfoil (smoothed) Max thickness 11.7% at 30% chord Max camber 4.7% at 35% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s2046-il) S2046		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord Max camber 2.6% at 55.1% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e195-il) E195 (11.82%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E195 low Reynolds number airfoil Max thickness 11.8% at 35% chord Max camber 2.7% at 44.2% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq208-il) HQ 2.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(isa960-il) I.S.A. 960		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 55.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database