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Numerical methods for the simulation of complex multi-body flows with applications for the integrated Space Shuttle vehicleThis project forms part of the long term computational effort to simulate the time dependent flow over the integrated Space Shuttle vehicle (orbiter, solid rocket boosters (SRB's), external tank (ET), and attach hardware) during its ascent mode for various nominal and abort flight conditions. Due to the limitations of experimental data such as wind tunnel wall effects and the difficulty of safely obtaining valid flight data, numerical simulations are undertaken to supplement the existing data base. This data can then be used to predict the aerodynamic behavior over a wide range of flight conditions. Existing computational results show relatively good overall comparison with experiments but further refinement is required to reduce numerical errors and to obtain finer agreements over a larger parameter space. One of the important goals of this project is to obtain better comparisons between numerical simulations and experiments. In the simulations performed so far, the geometry has been simplified in various ways to reduce the complexity so that useful results can be obtained in a reasonable time frame due to limitations in computer resources. In this project, the finer details of the major components of the Space Shuttle are modeled better by including more complexity in the geometry definition. Smaller components not included in early Space Shuttle simulations will now be modeled and gridded.
Document ID
19920021497
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Chan, William M.
(MCAT Inst. San Jose, CA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1992
Publication Information
Publication: Numerical Methods for the Simulation of Complex Multi-Body Flows with Applications for the Integrated Space Shuttle Vehicle
Subject Category
Aerodynamics
Accession Number
92N30741
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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