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NASA Technical Reports Server (NTRS) 19890003451: Aerodynamic press...
by NASA Technical Reports Server (NTRS)
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An aerothermal study was performed in the Langley 8-Foot
High Temperature Tunnel at Mach number 6.6 to define the
pressures and heating rates on the surfaces between split
elevons similar to those used on the Space Shuttle. Tests
were performed with both laminar and turbulent boundary
layers on the wing surface upstream of the elevons. The
flow in the chordwise gap between the elevons was
characterized by flow separation at the gap entrance and
flow reattachment at a depth into the gap inversely
proportional to the gap width. The gap pressure and
heating rate increased significantly with decrease of
elevon gap width, and the maximum gap heating rate was
proportional to the maximum gap pressure. Correlation of
the present results indicate that the gap heating was
directly proportional to the elevon windward surface
pressure and was not dependent upon whether the boundary
layer on the windward elevon surface was laminar or
turbulent.
Date Published: 2016-09-21 17:28:45
Identifier: NASA_NTRS_Archive_19890003451
Item Size: 74780551
Language: english
Media Type: texts
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