Computations of interacting flowfield of supersonic opposing jet with subsonic freestream around the base region of a vertical-lander space vehicle are carried out. The Naveir-Stokes equations in axisymmetric form with one equation turbulence model are solved by the upwind finite volume method. Calculated results show that there appears a vortex ring around the jet flow near the base region. It is shown in this study that the reduction of drag force with jet ejection is occurred by both the reduced base pressure due to the vortex ring that covers the base region, and the increased pressure along the side surface due to pressure recovery. The change of drag coefficient in response to varying amount of jet thrust is also shown to agree qualitatively with experimental data.
|Number of pages||9|
|Publication status||Published - 2004|
|Event||42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States|
Duration: 2004 Jan 5 → 2004 Jan 8
|Other||42nd AIAA Aerospace Sciences Meeting and Exhibit|
|Period||04/1/5 → 04/1/8|
ASJC Scopus subject areas