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, by Thomas L. Fischetti et al.

Title:	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.
Author:	United States. National Adviosry Committee for Aeronautics
Author:	Langley Aeronautical Laboratory
Author:	United States. National Advisory Committee for Aeronautics
Note:	National Advisory Committee for Aeronautics, 1957

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Subject:	Aerodynamic load
Subject:	Aerofoils -- Testing
Subject:	Airplanes -- Fuselage
Subject:	Airplanes -- Models -- Testing
Subject:	Airplanes -- Wings, Swept-back
Subject:	Charts, diagrams, etc.
Subject:	Fuselages
Subject:	Wind tunnel testing
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