Numerical study of hypersonic leeward flow over a blunt nosed delta wing

Sie sind hier: Homepage > Suche

Numerical study of hypersonic leeward flow over a blunt nosed delta wing

Mallett, E.R. / Pullin, D.I. / Macrossan, M.N.

The desig of reusable spacecraft such as the Hermes (currently under consideration by the European Space Agency) will be enhanced by an accurate computational prediction of the flowfield during hypersonic re-entry into the atmosphere. This is particularly important on the leeward side of lifting surfaces where vortex phenomena have been judged responsible for intense local heating. A kinetic theory based Navier-Stokes solver has been implemented on a parallel supercomputer (Intel iPSC Touchstone Delta) to study the leeward flowfield of a blunt nosed delta wing at 30-deg incidence at hypersonic speeds. Computational Results are presented for a series of grids for both inviscid and laminar viscous flows. Our present aim is to make a detailed comparison of the shock structure generated above the leeward surface for the inviscid and laminar viscous flows at Reynolds numbers of 2.25x10⁵ and 2.25x10⁶. In addition, comparisons are made between the present and other independant calculations of the same flows.