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Aerothermal loads analysis for high speed flow over a quilted surface configurationAttention is given to hypersonic laminar flow over a quilted surface configuration that simulates an array of Space Shuttle Thermal Protection System panels bowed in a spherical shape as a result of thermal gradients through the panel thickness. Pressure and heating loads to the surface are determined. The flow field over the configuration was mathematically modeled by means of time-dependent, three-dimensional conservation of mass, momentum, and energy equations. A boundary mapping technique was then used to obtain a rectangular, parallelepiped computational domain, and an explicit MacCormack (1972) explicit time-split predictor-corrector finite difference algorithm was used to obtain steady state solutions. Total integrated heating loads vary linearly with bowed height when this value does not exceed the local boundary layer thickness.
Document ID
19840055232
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Olsen, G. C.
(NASA Langley Research Center Hampton, VA, United States)
Smith, R. E.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-1630
Accession Number
84A38019
Distribution Limits
Public
Copyright
Other

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