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.

(goe323-il) GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 323 (Hansa-Brandenburg V.1) airfoil Max thickness 11.1% at 29.8% chord Max camber 5.2% at 29.8% chord Max Cl/Cd 54.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe315-il) GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 315 (Hansa-Brandenburg III.5) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 54.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(isa571-il) I.S.A. 571		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 571 airfoil Max thickness 7.4% at 30% chord Max camber 3.6% at 30% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx75141-il) WORTMANN FX 75-141		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 75-141 airfoil Max thickness 14.1% at 37.1% chord Max camber 3.4% at 53.3% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe490-il) GOE 490 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 490 airfoil Max thickness 8.8% at 19.9% chord Max camber 3.8% at 39.9% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe113-il) GOE 113 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 113 airfoil Max thickness 6.7% at 30% chord Max camber 3% at 40% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m25-il) NACA M25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe140-il) GOE 140 (MVA H.17) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 140 (MVA H.17) airfoil Max thickness 8.8% at 29.9% chord Max camber 5.3% at 29.9% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq2010-il) HQ 2.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2% at 45% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s4233-il) S4233-136-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord Max camber 2.7% at 48.8% chord Max Cl/Cd 54.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database