Time-accurate solution of the nonreacting compressible Navier Stokes equations have been obtained through the use of an implicit numerical algorithm; a subiteration procedure is implemented in the algorithm to achieve time accuracy. The numerical code is readily vectorizable, may be run at large CFL numbers, and thus is suited to the conduct of parametric studies. Laminar and transitional flows over three different cavity geometries were examined. The time-mean predictions showed good agreement with the available experimental data. Relatively large heat transfer rates and static pressure variations are observed in the rear part of the cavity. These gradients are associated with the large vortex structures in the rear of the cavity. For the high Reynolds number transitional flow, self-sustained flow oscillations were observed. The amplitudes of the oscillations are observed to increase with cavity length-to-depth ratio. These oscillations are associated with disturbances generated at the front of the cavity and pressure waves that propagate upstream from the rear of the cavity. However, unlike the lower speed cavity flows, no significant mass exchange is observed at the cavity rear. This work is the first phase of an effort to examine hypersonic cavity flows. In subsequent work, the effects of fine-scale turbulence will be included and the numerical algorithm extended to three dimensions.
Hypersonic flow past open cavities
Hypersonische Strömung um einen Hohlraum
AIAA Journal ; 32 , 12 ; 2387-2393
1994
7 Seiten, 18 Bilder, 1 Tabelle, 12 Quellen
Article (Journal)
English
Hypersonic flow past open cavities
NTRS | 1994
|Hypersonic flow past open cavities
AIAA | 1993
|Hypersonic Flow Past Open Cavities
Online Contents | 1994
|Hypersonic Flow Past Open Cavities
British Library Conference Proceedings | 1993
|Hypersonic flow past open cavities
AIAA | 1994
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