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Space Shuttle orbiter trimmed center-of-gravity extension studyAerodynamic, heat transfer, and system design studies to determine removable modifications for the Space Shuttle orbiter that would extend its forward center-of-gravity triom capability are summarized. Wind-tunnel tests were conducted at Mach numbers ranging from 0.25 to 20.3 to determine the most effective aerodynamic modifications. Heat transfer and system design studies determined the impact of the modifications on the thermal protection system and structural weight of the vehicle. The most effective modifications were in-fillet canards or a forward extension of the existing forward wing fillet.
Document ID
19850010693
Document Type
Technical Publication (TP)
Authors
Scallion, W. I. (NASA Langley Research Center Hampton, VA, United States)
Phillips, W. P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1985
Subject Category
LAUNCH VEHICLES AND SPACE VEHICLES
Report/Patent Number
L-15701
NAS 1.60:2284
NASA-TP-2284
Funding Number(s)
PROJECT: RTOP 506-51-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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