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.

(giiia-il) GIII BL0 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 11% at 39.7% chord Max camber 0.7% at 14.7% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e333-il) EPPLER 333 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E333 flying wing airfoil Max thickness 11.7% at 31.3% chord Max camber 3.5% at 26.4% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rae103-il) RAE 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca632615-il) NACA 63(2)-615		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-615 airfoil Max thickness 15% at 34.8% chord Max camber 3.3% at 50% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rhodesg36-il) Rhode St. Genese 36		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 36 airfoil Max thickness 16.2% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ames01-il) NASA/AMES A-01 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c141a-il) LOCKHEED C-141 BL0 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 13% at 40.2% chord Max camber 1.1% at 64.5% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63415-il) NACA 63-415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe459-il) GOE 459 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 459 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(kc135a-il) KC-135 BL52.44 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord Max Cl/Cd 27.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database