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An analytical procedure for evaluating shuttle abort staging aerodynamic characteristicsAn engineering analysis and computer code (AERSEP) for predicting Space Shuttle Orbiter - HO Tank longitudinal aerodynamic characteristics during abort separation has been developed. Computed results are applicable at Mach numbers above 2 for angle-of-attack between plus or minus 10 degrees. No practical restrictions on orbiter-tank relative positioning are indicated for tank-under-orbiter configurations. Input data requirements and computer running times are minimal facilitating program use for parametric studies, test planning, and trajectory analysis. In a majority of cases AERSEP Orbiter-Tank interference predictions are as accurate as state-of-the-art estimates for interference-free or isolated-vehicle configurations. AERSEP isolated-orbiter predictions also show excellent correlation with data.
Document ID
19730018150
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Meyer, R.
(Grumman Aerospace Corp. Bethpage, NY, United States)
Date Acquired
September 2, 2013
Publication Date
May 31, 1973
Subject Category
Space Vehicles
Report/Patent Number
NASA-CR-128974
MSC-06085
Accession Number
73N26877
Funding Number(s)
CONTRACT_GRANT: NAS9-12581
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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