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Hybrid Methods in Engineering

ISSN 印刷: 1099-2391
ISSN オンライン: 2641-7359

Archives: Volume 1, 1999 to Volume 4, 2002

Hybrid Methods in Engineering

DOI: 10.1615/HybMethEng.v1.i3.30
14 pages

SELF-SIMILAR COMPRESSIBLE LAMINAR BOUNDARY LAYERS BEHIND A NORMAL SHOCK WAVE ADVANCING INTO A STATIONARY FLUID

P. G. P. Toro
Institute de Aeronaútica e Espaço - IAE - Centre Técnico Aeroespacial - CTA São José dos Campos - SP 12228-904 - Brazil
Z. Rusak
Department of Mechanical Engineering, Aeronautical Engineering, and Mechanics, Rensselaer Polytechnic Institute, Troy, NY 12180-3590 - USA
H. T. Nagamatsu
Department of Mechanical Engineering, Aeronautical Engineering, and Mechanics, Rensselaer Polytechnic Institute, Troy, NY 12180-3590 - USA
L. N. Myrabo
Department of Mechanical Engineering, Aeronautical Engineering, and Mechanics, Rensselaer Polytechnic Institute, Troy, NY 12180-3590 - USA

要約

A new methodology of deriving a self-similar solution of the compressible laminar boundary layer equations is applied to investigate the airflow behind a normal shock wave advancing into a stationary fluid bounded by a solid wall. Modified Levy-Mangier and Dorodnitsyn-Howarth transformations are used to solve the boundary layer flow on a smooth flat plate with no external pressure gradient. These transformations describe the similarity variables in terms of a power of the density that appears in the viscosity-temperature power law relation. This results in an explicit relation between the stream function and the temperature fields described by a closed coupled system of nonlinear ordinary differential equations. Solutions of the velocity and temperature profiles and the influence of the wall to external flow temperature ratio are presented for various shock wave strengths.


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