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.

(rg15-il) RG-15 8.9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 15 low Reynolds number airfoil Max thickness 8.9% at 30.2% chord Max camber 1.8% at 39.7% chord Max Cl/Cd 63.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s5010-il) S5010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord Max camber 1.8% at 32% chord Max Cl/Cd 63.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa51-il) USA 51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-51 airfoil Max thickness 9.3% at 30% chord Max camber 2.6% at 30% chord Max Cl/Cd 63.2 at Re# 200,000 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 63.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n64215-il) NACA 64-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 63.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(naca642215-il) NACA 64(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 63.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe320-il) GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 320 (Hansa-Brandenburg II.1) airfoil Max thickness 12.3% at 29.8% chord Max camber 6.2% at 29.8% chord Max Cl/Cd 63.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m9-il) NACA M9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord Max camber 7.2% at 30% chord Max Cl/Cd 63.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq1010-il) HQ 1.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 63.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(c141b-il) LOCKHEED C-141 BL113.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 12.6% at 40.2% chord Max camber 1.1% at 64.5% chord Max Cl/Cd 63.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database