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Supersonic flow onto a solid wedge
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DOI：10.1002/cpa.20231.png)
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Abstract
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We consider the problem of two-dimensional supersonic flow onto a solid wedge, or equivalently in a concave corner formed by two solid walls. For mild corners, there are two possible steady state solutions, one with a strong and one with a, weak shock emanating from the corner. The weak shock is observed in supersonic flights. A longstanding natural conjecture is that the strong shock is unstable in some sense. We resolve this issue by showing that a sharp wedge will eventually produce weak shocks at the tip when accelerated to a supersonic speed. More precisely, we prove that for upstream state as initial data in the entire domain, the time-dependent solution is self-similar, with a weak shock at the tip of the wedge. We construct analytic solutions for self-similar potential flow, both isothermal and isentropic with arbitrary gamma >= 1. In the process of constructing the self-similar Solution, we develop a large number of theoretical tools tor these elliptic regions. These tools allow LIS to establish large-data results rather than a small perturbation. We show that the wave pattern persists as long as the weak shock is supersonic-supersonic; when this is no longer true, numerics show a physical change of behavior. In addition, we obtain rather detailed information about the elliptic region, including analyticity as well as bounds for velocity components and shock tangents. (c) 2007 Wiley Periodicals, Inc.
Keywords:
FREE-BOUNDARY PROBLEM
ELLIPTIC EQUATION
TRANSONIC SHOCKS
STABILITY
EXISTENCE
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