Computational analysis of opposing jet from vertical-lander space vehicle

Teruhiko Kitamura, Naofumi Ohnishi, Keisuke Sawada

Research output: Contribution to conferencePaperpeer-review

2 Citations (Scopus)


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.

Original languageEnglish
Number of pages9
Publication statusPublished - 2004
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: 2004 Jan 52004 Jan 8


Conference42nd AIAA Aerospace Sciences Meeting and Exhibit
Country/TerritoryUnited States
CityReno, NV


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