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Flow fields and aerodynamic characteristics for hypersonic missiles with mid-fuselage inletsA study was made to quantify forebody flow fields and to evaluate aerodynamic performance trends on a matrix of fuselage shapes for the mid-inlet/bolt-on-engine class of hypersonic airbreathing missiles for the Navy's vertical box launcher. The study indicated that inlet mass flow and pressure recovery can be increased by cambering the nose and increasing the width of the fuselage at both Mach 4 acceleration and Mach 6 cruise conditions. Aerodynamic trim predictions show that the drag at zero lift at Mach 4 decreases while the L/D max at Mach 6 increases with the nose camber, although these tendencies reverse with increasing width of maximum fuselage cross section.
Document ID
19830035559
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hunt, J. L.
(NASA Langley Research Center Hampton, VA, United States)
Johnston, P. J.
(NASA Langley Research Center Hampton, VA, United States)
Riebe, G. D.
(NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 83-0542
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Reno, NV
Start Date: January 10, 1983
End Date: January 13, 1983
Accession Number
83A16777
Distribution Limits
Public
Copyright
Other

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