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Advances in Hypersonics pp 220–298Cite as

Birkhäuser

Numerical Simulation of Entry Flow over Blunt Swept-Wing Planes

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Abstract

Viscous, heat-conducting flow with chemical and vibrational relaxation processes of the constituent gases surrounding winged spacecraft is considered in the continuum regime. The Navier-Stokes equations are appended by additional vibrational energy and species rate equations and supplemented by the equations of state and the phenomenological laws based on mixture rules or collisional cross sections. Numerical convective flux can be obtained from several forms of one-dimensional Riemann solver , with or without entropy correction. High-order accuracy is obtained from two types of reconstructive interpolation. A number of explicit and implicit numerical schemes have been implemented as a means to yield converged solutions. Both shock-fitting, finite-difference and shock-capturing, finitevolume techniques have been tested for configurations such as a sphere, double ellipsoid, blunt-edge delta wing, a European Hermes vehicle, and the U .S. Shuttle orbiter. The shock-fitting code provides excellent results only for simple configurations, whereas the shock-capturing code leads to overall satisfying solutions for complex geometries. The ADI or LU factorization technique using a local time increment up to the Courant number equal to 4 has facilitated inviscid, reacting flow simulations on a Convex 2 or Cray XMP. Yet viscous and thermochemical nonequilibrium flow computations require prohibitively large memory sizes and unavailable computer speeds; hence only a few cases of practical interest are shown.

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Authors
  1. C. P. Li
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Editors and Affiliations

  1. Sandia National Laboratories, Albuquerque, NM 87111, USA

    John J. Bertin

  2. Dept. of Aerodynamic Theory Avions Marcel Dassault-Brequet Aviation, 92214 Saint Cloud, France

    Jacques Periaux

  3. Lehr-Und Forschungsbiet für Mechanik der Rheinisch-Westfälischen, Technischen Hochschule Aachen, Templergraben 64, Germany

    Josef Ballmann

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© 1992 Springer Science+Business Media New York

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Li, C.P. (1992). Numerical Simulation of Entry Flow over Blunt Swept-Wing Planes. In: Bertin, J.J., Periaux, J., Ballmann, J. (eds) Advances in Hypersonics. Birkhäuser, Boston, MA. https://doi.org/10.1007/978-1-4612-0375-9_5

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  • DOI: https://doi.org/10.1007/978-1-4612-0375-9_5

  • Publisher Name: Birkhäuser, Boston, MA

  • Print ISBN: 978-1-4612-6732-4

  • Online ISBN: 978-1-4612-0375-9

  • eBook Packages: Springer Book Archive

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