An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47©� sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel

Document details

Author:	Bielat, Ralph P.
Additional Authors:	Harrison, Daniel E., Coppolino, Domenic A.
Year:	1951
Document Type:	NACA
Issuing Agency:	National Advisory Committee for Aeronautics,
SUDOC:	Y 3.N 21/5:15/L51I04a
Series:	NACA research memorandum ;
Report Number:	L51I04a
Subjects:	Charts, diagrams, etc
	Lift (Aerodynamics)
	Wind tunnel testing
	Drag (Aerodynamics)
	Airplanes--Fuselage
	Airplanes--Wings, Swept-back
	Aerodynamics, Transonic
Link:	https://hdl.handle.net/2027/mdp.39015086506873

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