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.

(eh1090-il) EH 1.0/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1% at 25.9% chord Max Cl/Cd 73.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e186-il) E186 (10.27%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E186 low Reynolds number airfoil Max thickness 10.2% at 29% chord Max camber 0.8% at 29% chord Max Cl/Cd 73.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 73.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m4-il) NACA M4 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-4 airfoil Max thickness 6.3% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 73.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(dsma523b-il) DSMA-523B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord Max Cl/Cd 73.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(usa48-il) USA 48 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-48 airfoil Max thickness 14.9% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 73.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m665-il) M6 (65%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (65%) Max thickness 7.8% at 30% chord Max camber 1.4% at 30% chord Max Cl/Cd 73.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s8066-il) S8066 (10% version of S8065 w/ lower surface aerodynamically similar)		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 (10%). Max thickness 10% at 37.7% chord Max camber 0.8% at 56.3% chord Max Cl/Cd 73.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca64a210-il) NACA 64A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Max Cl/Cd 73.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n14-il) N-14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord Max Cl/Cd 73.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database