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.

(goe374-il) GOE 374 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 374 airfoil Max thickness 6.5% at 30% chord Max camber 4.5% at 30% chord Max Cl/Cd 74.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe413-il) GOE 413 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 413 airfoil Max thickness 16.4% at 30% chord Max camber 4.6% at 40% chord Max Cl/Cd 74.5 at Re# 200,000 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 74.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe448-il) GOE 448 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 448 airfoil Max thickness 12.9% at 29.8% chord Max camber 10.5% at 39.8% chord Max Cl/Cd 74.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 74.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe414-il) GOE 414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 414 airfoil Max thickness 13.6% at 29.7% chord Max camber 5.3% at 39.7% chord Max Cl/Cd 74.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe574-il) GOE 574 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 574 airfoil Max thickness 10.3% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 74.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah79k135-il) AH 79-K-135/20 B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-135/20 airfoil for use with flaps (K) Max thickness 13.5% at 40.2% chord Max camber 3.1% at 40.2% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(gs1-il) SIKORSKY GS-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s4083-il) S4083 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database