Computation of Flow Past Conical Hypersonic Wings Using a Second Order Godunov Method,
IMPERIAL COLL OF SCIENCE AND TECHNOLOGY LONDON (UNITED KINGDOM) DEPT OF AERON AUTICS
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This paper presents computations of inviscid hypersonic flow past flat plate delta wings using a second order Godunov-type scheme. The governing equations are written in an unsteady conical form and then time-marched to a final conical steady state. The core of of the calculation is a generalised Riemann problem which is used to determine the flux transfers at the interfaces between computational cells. Results are presented for wings with shock waves both attached at and detached from the leading edges. The leeward surface flows support embedded shock waves and separated vortex flows and the likely influence of real viscous effects on these is discussed.
- Fluid Mechanics