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.

(goe624-il) GOE 624 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 624 airfoil Max thickness 16% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 69.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe565-il) GOE 565 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 565 airfoil Max thickness 8.4% at 30% chord Max camber 2.8% at 50% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf38-il) RAF 38 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-38 airfoil Max thickness 12.7% at 30% chord Max camber 2.5% at 40% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe284-il) GOE 284 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 284 airfoil Max thickness 17.7% at 29.3% chord Max camber 5.1% at 39.3% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe318-il) GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 318 (Hansa-Brandenburg VI.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.3% at 29.9% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe530-il) GOE 530 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 530 airfoil Max thickness 12.9% at 29.8% chord Max camber 5.1% at 29.8% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa27-il) USA 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s8065-il) S8065 (11% version of S8064)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-40 pylon racing (11%). Max thickness 11% at 37.8% chord Max camber 1.1% at 56.3% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e554-il) EPPLER 554 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord Max camber 2.7% at 56.6% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe290-il) GOE 290 (MVA 290) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 290 (MVA 290) airfoil Max thickness 17.6% at 29.1% chord Max camber 3.9% at 39.2% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database