Abstract
The physics of the plume-induced shock and separation, particularly at high plume to exit pressure ratios with and without shock-turbulent boundary-layer control methods, were studied using computational techniques. Mass-averaged Navier-Stokes equations with a two-equation turbulence model were solved by using a fully implicit finite volume scheme and time.marching algorithm. The control methodologies for shock interactions included a porous tail and a porous extension attached at the nozzle exit or trailing edge. The porous tail produced a weaker shock and fixed the shock position on the control surface. The effect of the porous extension on shock interactions was mainly to restrain the plume from strongly underexpanding during a change in flight conditions. These techniques could give an additional dimension to the design and control of supersonic missiles.
Original language | English |
---|---|
Pages (from-to) | 1653-1662 |
Number of pages | 10 |
Journal | AIAA Journal |
Volume | 43 (8) |
Issue number | 8 |
Publication status | Published - Aug 2005 |
ASJC Scopus subject areas
- Aerospace Engineering