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.

(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 39.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe802b-il) GOE 802 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 39.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe361-il) GOE 361 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 361 airfoil Max thickness 6.8% at 20% chord Max camber 5.5% at 40% chord Max Cl/Cd 39.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(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 39.3 at Re# 50,000 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 39.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(hq309-il) HQ 3.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 39.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s4110-il) S4110		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord Max Cl/Cd 39.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s4053-il) S4053		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4053 low Reynolds number airfoil Max thickness 8.9% at 30.9% chord Max camber 3% at 45% chord Max Cl/Cd 39.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1221-flap-il) S1221 w/ 4 deg flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord Max Cl/Cd 39.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe602m-il) GOE 602 MOD. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 602 MOD airfoil Max thickness 9.6% at 30% chord Max camber 3.8% at 50% chord Max Cl/Cd 39.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database