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.

(goe09k-il) GOE 9K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord Max Cl/Cd 63.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq09-il) HQ 0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 63.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m1-il) NACA-M1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 63.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 63.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s4096-il) S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 12.5% at 34% chord Max camber 1.2% at 34% chord Max Cl/Cd 63.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(naca64a010-il) NACA 64A-010 10.0%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A010 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 63.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(lwk80120k25-il) LWK 80-120/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-120/K25 symmetrical airfoil Max thickness 12.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 63.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca001264-il) NACA 0012-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 63 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe571-il) GOE 571 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 571 airfoil Max thickness 24.9% at 29.4% chord Max camber 9.8% at 29.4% chord Max Cl/Cd 62.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(nplx-il) NPL AIRFOIL FROM ARC CP 1372		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL transonic airfoil FROM ARC CP 1372 Max thickness 10.7% at 35.8% chord Max camber 1.1% at 73.7% chord Max Cl/Cd 62.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database