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.

(goe590-il) GOE 590 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 590 airfoil Max thickness 5.7% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord Max camber 4.5% at 30% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe362-il) GOE 362 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 362 airfoil Max thickness 6.6% at 20% chord Max camber 5.3% at 40% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq2195-il) HQ 2.1/9.5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa22-il) USA 22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(coanda3-il) Coanda 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 3 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe116-il) GOE 116 (MVA MK.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe310-il) GOE 310 (MVA H.42) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.8% at 39.9% chord Max Cl/Cd 37.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s2048-il) S2048		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2048 low Reynolds number airfoil Max thickness 8.6% at 35.4% chord Max camber 1.7% at 60.1% chord Max Cl/Cd 37.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe415-il) GOE 415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 415 airfoil Max thickness 8.5% at 19.9% chord Max camber 3.7% at 29.9% chord Max Cl/Cd 37.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database