Parallel finite element computation of missile aerodynamics

W. B. Sturek, S. Ray, S. Aliabadi, C. Waters, Tayfun E. Tezduyar

Research output: Contribution to journalArticle

Abstract

A flow simulation tool, developed by the authors at the Army HPC Research Center, for compressible flows governed by the Navier-Stokes equations is used to study missile aerodynamics at supersonic speeds, high angles of attack and for large Reynolds numbers. The goal of this study is the evaluation of this Navier-Stokes computational technique for the prediction of separated flow fields around high-length-to-diameter (L/D) bodies. In particular, this paper addresses two issues: (i) turbulence modelling with a finite element computational technique and (ii) efficient performance of the computational technique on two different multiprocessor mainframes, the Thinking Machines CM-5 and CRAY T3D. The paper first provides a discussion of the Navier-Stokes computational technique and the algorithm issues for achieving efficient performance on the CM-5 and T3D. Next, comparisons are shown between the computation and experiment for supersonic ramp flow to evaluate the suitability of the turbulence model. Following that, results of the computations for missile flow fields are shown for laminar and turbulent viscous effects.

Original languageEnglish
Pages (from-to)1417-1432
Number of pages16
JournalInternational Journal for Numerical Methods in Fluids
Volume24
Issue number12
Publication statusPublished - 1997 Jun 30
Externally publishedYes

Fingerprint

Computational Techniques
missiles
Missile
Missiles
aerodynamics
Aerodynamics
Flow fields
flow distribution
supersonic speed
Finite Element
separated flow
compressible flow
Compressible flow
angle of attack
Flow simulation
turbulence models
Angle of attack
ramps
Turbulence models
Navier-Stokes

Keywords

  • Compressible flows
  • Missile aerodynamics
  • Parallel computing methods

ASJC Scopus subject areas

  • Computational Theory and Mathematics
  • Computer Science Applications
  • Computational Mechanics
  • Mechanics of Materials
  • Safety, Risk, Reliability and Quality
  • Applied Mathematics
  • Condensed Matter Physics

Cite this

Parallel finite element computation of missile aerodynamics. / Sturek, W. B.; Ray, S.; Aliabadi, S.; Waters, C.; Tezduyar, Tayfun E.

In: International Journal for Numerical Methods in Fluids, Vol. 24, No. 12, 30.06.1997, p. 1417-1432.

Research output: Contribution to journalArticle

Sturek, WB, Ray, S, Aliabadi, S, Waters, C & Tezduyar, TE 1997, 'Parallel finite element computation of missile aerodynamics', International Journal for Numerical Methods in Fluids, vol. 24, no. 12, pp. 1417-1432.
Sturek, W. B. ; Ray, S. ; Aliabadi, S. ; Waters, C. ; Tezduyar, Tayfun E. / Parallel finite element computation of missile aerodynamics. In: International Journal for Numerical Methods in Fluids. 1997 ; Vol. 24, No. 12. pp. 1417-1432.
@article{53be1601c870416bbb44b6d1466b4398,
title = "Parallel finite element computation of missile aerodynamics",
abstract = "A flow simulation tool, developed by the authors at the Army HPC Research Center, for compressible flows governed by the Navier-Stokes equations is used to study missile aerodynamics at supersonic speeds, high angles of attack and for large Reynolds numbers. The goal of this study is the evaluation of this Navier-Stokes computational technique for the prediction of separated flow fields around high-length-to-diameter (L/D) bodies. In particular, this paper addresses two issues: (i) turbulence modelling with a finite element computational technique and (ii) efficient performance of the computational technique on two different multiprocessor mainframes, the Thinking Machines CM-5 and CRAY T3D. The paper first provides a discussion of the Navier-Stokes computational technique and the algorithm issues for achieving efficient performance on the CM-5 and T3D. Next, comparisons are shown between the computation and experiment for supersonic ramp flow to evaluate the suitability of the turbulence model. Following that, results of the computations for missile flow fields are shown for laminar and turbulent viscous effects.",
keywords = "Compressible flows, Missile aerodynamics, Parallel computing methods",
author = "Sturek, {W. B.} and S. Ray and S. Aliabadi and C. Waters and Tezduyar, {Tayfun E.}",
year = "1997",
month = "6",
day = "30",
language = "English",
volume = "24",
pages = "1417--1432",
journal = "International Journal for Numerical Methods in Fluids",
issn = "0271-2091",
publisher = "John Wiley and Sons Ltd",
number = "12",

}

TY - JOUR

T1 - Parallel finite element computation of missile aerodynamics

AU - Sturek, W. B.

AU - Ray, S.

AU - Aliabadi, S.

AU - Waters, C.

AU - Tezduyar, Tayfun E.

PY - 1997/6/30

Y1 - 1997/6/30

N2 - A flow simulation tool, developed by the authors at the Army HPC Research Center, for compressible flows governed by the Navier-Stokes equations is used to study missile aerodynamics at supersonic speeds, high angles of attack and for large Reynolds numbers. The goal of this study is the evaluation of this Navier-Stokes computational technique for the prediction of separated flow fields around high-length-to-diameter (L/D) bodies. In particular, this paper addresses two issues: (i) turbulence modelling with a finite element computational technique and (ii) efficient performance of the computational technique on two different multiprocessor mainframes, the Thinking Machines CM-5 and CRAY T3D. The paper first provides a discussion of the Navier-Stokes computational technique and the algorithm issues for achieving efficient performance on the CM-5 and T3D. Next, comparisons are shown between the computation and experiment for supersonic ramp flow to evaluate the suitability of the turbulence model. Following that, results of the computations for missile flow fields are shown for laminar and turbulent viscous effects.

AB - A flow simulation tool, developed by the authors at the Army HPC Research Center, for compressible flows governed by the Navier-Stokes equations is used to study missile aerodynamics at supersonic speeds, high angles of attack and for large Reynolds numbers. The goal of this study is the evaluation of this Navier-Stokes computational technique for the prediction of separated flow fields around high-length-to-diameter (L/D) bodies. In particular, this paper addresses two issues: (i) turbulence modelling with a finite element computational technique and (ii) efficient performance of the computational technique on two different multiprocessor mainframes, the Thinking Machines CM-5 and CRAY T3D. The paper first provides a discussion of the Navier-Stokes computational technique and the algorithm issues for achieving efficient performance on the CM-5 and T3D. Next, comparisons are shown between the computation and experiment for supersonic ramp flow to evaluate the suitability of the turbulence model. Following that, results of the computations for missile flow fields are shown for laminar and turbulent viscous effects.

KW - Compressible flows

KW - Missile aerodynamics

KW - Parallel computing methods

UR - http://www.scopus.com/inward/record.url?scp=0031171048&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0031171048&partnerID=8YFLogxK

M3 - Article

AN - SCOPUS:0031171048

VL - 24

SP - 1417

EP - 1432

JO - International Journal for Numerical Methods in Fluids

JF - International Journal for Numerical Methods in Fluids

SN - 0271-2091

IS - 12

ER -