Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies

Author:	Fischetti, Thomas L.
Year:	1957
Document Type:	NACA
Issuing Agency:	National Advisory Committee for Aeronautics,
SUDOC:	Y 3.N 21/5:15/L57D29A
Series:	NACA research memorandum ;
Report Number:	L57D29A
Subjects:	Charts, diagrams, etc
	Aerodynamic load
	Wind tunnel testing
	Airplanes--Fuselage
	Airplanes--Wings, Swept-back
	Airplanes--Models--Testing
	Aerofoils--Testing
Link:	https://hdl.handle.net/2027/mdp.39015086466136