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.

(usa46-il) USA 46 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-46 airfoil Max thickness 6.5% at 20% chord Max camber 2.2% at 40% chord Max Cl/Cd 69 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s8037-il) S8037 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8037 low Reynolds number airfoil Max thickness 16% at 33.5% chord Max camber 1.9% at 40.4% chord Max Cl/Cd 69 at Re# 200,000 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 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd2030-il) SD2030-086-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD2030 low Reynolds number airfoil Max thickness 8.6% at 35.5% chord Max camber 2.2% at 45.3% chord Max Cl/Cd 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m16-il) NACA M16 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(kc135a-il) KC-135 BL52.44 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord Max Cl/Cd 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord Max Cl/Cd 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n10-il) N-10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-10 airfoil Max thickness 11.2% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s8064-il) 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-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord Max camber 1.1% at 56.2% chord Max Cl/Cd 68.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe509-il) GOE 509 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 509 airfoil Max thickness 11.1% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 68.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database