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.

(arad13-il) ARA-D 13% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord 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 Source UIUC Airfoil Coordinates Database
(mh201-il) MH 201 13.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord Source UIUC Airfoil Coordinates Database
(mh200-il) MH 200 12.97%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord Source UIUC Airfoil Coordinates Database
(rg15a213-il) RG 15A 2.5/13.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 15A 2.5/13.0 airfoil Max thickness 13% at 30.2% chord Max camber 2.5% at 39.7% chord Source UIUC Airfoil Coordinates Database

(hq3513-il) HQ 3.5/13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3.5% at 50% chord Source UIUC Airfoil Coordinates Database
(s8038-il) S8038 (13%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8038 (13%) low Reynolds number airfoil Max thickness 13% at 32.9% chord Max camber 0.6% at 40.1% chord Source UIUC Airfoil Coordinates Database
(e337-il) EPPLER 337 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E337 flying wing airfoil Max thickness 13.1% at 32% chord Max camber 3.2% at 22.4% chord Source UIUC Airfoil Coordinates Database
(goe600-il) GOE 600 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord Source UIUC Airfoil Coordinates Database
(goe412-il) GOE 412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 412 airfoil Max thickness 13.1% at 29.7% chord Max camber 5.1% at 39.7% chord Source UIUC Airfoil Coordinates Database