Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift

Author:	Morrow, John D.
Additional Authors:	Katz, Ellis.
Year:	1950
Document Type:	NACA
Issuing Agency:	National Advisory Committee for Aeronautics,
SUDOC:	Y 3.N 21/5:15/L50E19A
Series:	NACA research memorandum ;
Report Number:	L50E19A
Subjects:	Charts, diagrams, etc
	Aerodynamic load
	Mach number
	Drag (Aerodynamics)
	Aerodynamics, Supersonic
	Trailing edges (Aerodynamics)
	Aerofoils--Testing
Link:	https://hdl.handle.net/2027/mdp.39015086464651