Numerical simulation of the integrated space shuttle vehicle in ascent

P. G. Buning; I. T. Chiu; S. Obayashi; Y. M. Rizk; J. L. Steger

doi:10.2514/6.1988-4359

Numerical simulation of the integrated space shuttle vehicle in ascent

P. G. Buning, I. T. Chiu, S. Obayashi, Y. M. Rizk, J. L. Steger

Research output: Contribution to conference › Paper › peer-review

17 Citations (Scopus)

Abstract

A simulation of the flow about the integrated space shuttle vehicle in ascent mode has been undertaken for various flight conditions using the Chimera composite grid discretization approach. Overset body-conforming grids were used to represent each geometric component, and an implicit approximately factored finite-difference procedure was used to solve the three-dimensional thin-layer Navier-Stokes equations. The computational results have been compared with both wind tunnel and flight test data. Although relatively good agreement is obtained with the experimental data, further refinement and evaluation of numerical error is under way.

Original language	English
Pages	265-283
Number of pages	19
DOIs	https://doi.org/10.2514/6.1988-4359
Publication status	Published - 1988
Externally published	Yes
Event	15th Atmospheric Flight Mechanics Conference, 1988 - Minneapolis, United States Duration: 1988 Aug 15 → 1988 Aug 17

Other

Other	15th Atmospheric Flight Mechanics Conference, 1988
Country/Territory	United States
City	Minneapolis
Period	88/8/15 → 88/8/17

ASJC Scopus subject areas

Mechanical Engineering
Aerospace Engineering

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10.2514/6.1988-4359

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title = "Numerical simulation of the integrated space shuttle vehicle in ascent",

abstract = "A simulation of the flow about the integrated space shuttle vehicle in ascent mode has been undertaken for various flight conditions using the Chimera composite grid discretization approach. Overset body-conforming grids were used to represent each geometric component, and an implicit approximately factored finite-difference procedure was used to solve the three-dimensional thin-layer Navier-Stokes equations. The computational results have been compared with both wind tunnel and flight test data. Although relatively good agreement is obtained with the experimental data, further refinement and evaluation of numerical error is under way.",

author = "Buning, {P. G.} and Chiu, {I. T.} and S. Obayashi and Rizk, {Y. M.} and Steger, {J. L.}",

note = "Funding Information: Acknowledgments: The authors are indebted to Fred Martin, Jr., of the NASA Johnson Space Center; Shmuel Ben-Shmuel of Rockwell International; Jack Benek, Bill Deiss, and Norm Suhs of CALSPAN; Robert Meakin of Sterling Software; and Lewis Peach and Anthony Gross of the NASA Ames Research Center. Financial support was provided by the NASA Johnson Space Center, and the NASA Numerical Aerodynamic Simulation Program furnished GRAY 2 computer time for this undertaking. Publisher Copyright: {\textcopyright} 1998, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.; 15th Atmospheric Flight Mechanics Conference, 1988 ; Conference date: 15-08-1988 Through 17-08-1988",

year = "1988",

doi = "10.2514/6.1988-4359",

language = "English",

pages = "265--283",

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T1 - Numerical simulation of the integrated space shuttle vehicle in ascent

AU - Buning, P. G.

AU - Chiu, I. T.

AU - Obayashi, S.

AU - Rizk, Y. M.

AU - Steger, J. L.

N1 - Funding Information: Acknowledgments: The authors are indebted to Fred Martin, Jr., of the NASA Johnson Space Center; Shmuel Ben-Shmuel of Rockwell International; Jack Benek, Bill Deiss, and Norm Suhs of CALSPAN; Robert Meakin of Sterling Software; and Lewis Peach and Anthony Gross of the NASA Ames Research Center. Financial support was provided by the NASA Johnson Space Center, and the NASA Numerical Aerodynamic Simulation Program furnished GRAY 2 computer time for this undertaking. Publisher Copyright: © 1998, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

PY - 1988

Y1 - 1988

N2 - A simulation of the flow about the integrated space shuttle vehicle in ascent mode has been undertaken for various flight conditions using the Chimera composite grid discretization approach. Overset body-conforming grids were used to represent each geometric component, and an implicit approximately factored finite-difference procedure was used to solve the three-dimensional thin-layer Navier-Stokes equations. The computational results have been compared with both wind tunnel and flight test data. Although relatively good agreement is obtained with the experimental data, further refinement and evaluation of numerical error is under way.

AB - A simulation of the flow about the integrated space shuttle vehicle in ascent mode has been undertaken for various flight conditions using the Chimera composite grid discretization approach. Overset body-conforming grids were used to represent each geometric component, and an implicit approximately factored finite-difference procedure was used to solve the three-dimensional thin-layer Navier-Stokes equations. The computational results have been compared with both wind tunnel and flight test data. Although relatively good agreement is obtained with the experimental data, further refinement and evaluation of numerical error is under way.

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T2 - 15th Atmospheric Flight Mechanics Conference, 1988

Y2 - 15 August 1988 through 17 August 1988

ER -

Numerical simulation of the integrated space shuttle vehicle in ascent

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