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.

(bacxxx-il) BOEING BACXXX AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n5h10-il) NACA 5-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-10 rotorcraft airfoil Max thickness 9.9% at 40% chord Max camber 2.3% at 40% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(giiin-il) GIII BL450 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 8.4% at 30.2% chord Max camber 2.1% at 20.2% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord Max camber 3% at 29% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c5d-il) LOCKHEED C-5A BL758.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 60% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(nlf0115-il) NLF(1)-0115		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil Max thickness 15% at 44.1% chord Max camber 1.8% at 30% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sd7090-il) SD7090 (10%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7090 low Reynolds number airfoil Max thickness 10% at 29.3% chord Max camber 1.5% at 43.6% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag47c03-il) AG47c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47c -03f airfoil Max thickness 5.1% at 22.4% chord Max camber 1.3% at 33.4% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hor12-il) ONERA HOR12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord Max camber 3.7% at 46.2% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe430-il) GOE 430 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 430 airfoil Max thickness 13.4% at 29.5% chord Max camber 4.8% at 49.6% chord Max Cl/Cd 30.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database