Abstract This paper presents an overview of the physical and numerical aspects of flows encountered around a vehicle in hypersonic flight. These problems are typically related to the reentry phase of a space shuttle into the atmosphere. Nonetheless, it is believed that the material given here is a good background for other applications. Compared with the standard aerodynamic problems on an aircraft in transonic or supersonic flight, hypersonic flows are characterized by a much higher level of energy. The high temperature of the flow can lead to thermochemical non-equilibrium, with chemical reactions and vibrational relaxation. These effects are of prime importance in the evaluation of the heating of the body and they may affect general flow features, including the wall pressure. Basic elements are discussed to understand the physics of these phenomena. Applications are given in the framework of boundary layer calculations and of numerical solutions of the Navier-Stokes equations. In the front of the vehicle, a strong bow shock wave forms and the boundary layer is fed by a rotational flow. A discussion is given concerning how a boundary layer theory can account for these effects. At lower altitudes, the velocity of the flow remains large, the Reynolds number increases and the flow becomes turbulent. In this context, laminar-turbulent transition and turbulence modelling are discussed.
Shock layers and boundary layers in hypersonic flows
1993-07-26
118 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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