Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(naca632a015-il) NACA 63(2)A-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord Max camber 1.7% at 14.6% chord Max Cl/Cd 45.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq1012-il) HQ 1.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 45.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe506-il) GOE 506 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 506 airfoil Max thickness 16.5% at 29.3% chord Max camber 4.7% at 39.3% chord Max Cl/Cd 45.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sd7003-il) SD7003-085-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7003 low Reynolds number airfoil Max thickness 8.5% at 24.4% chord Max camber 1.2% at 38.3% chord Max Cl/Cd 45.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(pmc19sm-il) PMC19 Smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	PMC19 Max thickness 9.2% at 34.2% chord Max camber 2.1% at 17.5% chord Max Cl/Cd 45 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(giiil-il) GIII BL387 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.1% chord Max camber 1.6% at 25.1% chord Max Cl/Cd 45 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq109-il) HQ 1.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord Max Cl/Cd 45 at Re# 100,000 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 45 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh60-il) MH 60 10.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 45 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx74130wp2mod-il) 74-130 WP2 MOD		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann 74-130 WP2 MOD airfoil Max thickness 12.9% at 43.5% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 45 at Re# 100,000 Source UIUC Airfoil Coordinates Database