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.

(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Max Cl/Cd 89.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe564-il) GOE 564 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 564 airfoil Max thickness 8.2% at 30% chord Max camber 2.7% at 40% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(p51dtip-il) P-51D TIP (BL215) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(bw3-il) Bergey BW-3 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bergey BW-3 wind turbine airfoil (smoothed) Max thickness 5% at 7.4% chord Max camber 5.7% at 45.4% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(ag17-il) AG17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG17 airfoil Max thickness 6.5% at 22.1% chord Max camber 2% at 45.5% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(pt40-il) PT40		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe507-il) GOE 507 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 89.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(kc135winglet-il) KC-135 Winglet (supercritical Whitcomb)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb Max thickness 8% at 40% chord Max camber 2.7% at 65% chord Max Cl/Cd 89.1 at Re# 1,000,000 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 89.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database