The oscillations of the flow field around a hemispherical nose with a supersonic opposing jet in a free stream of Mach 3.98 are computed. Two total pressure ratios of a jet to a free stream 0.2 and 0.6 are examined, which correspond to unsteady flow and steady flow, respectively. The axisymmetric Navier-Stokes equations with Shear-Stress Transport (SST) turbulence model are used as the governing equations in this paper. The oscillations of the flow field are reproduced, and mechanism of the oscillations is analyzed. Time-accurate algorithm is found to be necessary when an opposing jet flow field is solved, even for stable flow field. The time-averaged density distribution obtained in this paper is in good agreement with schlieren photograph. Also, the wall heat flux predicted in this paper is in agreement with experimental result.
The study on oscillations of an opposing jet flow
2008-12-01
3277510 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Axisymmetric Oscillations of an Opposing Jet from a Hemispherical Nose
British Library Conference Proceedings | 1994
|Axisymmetric Oscillations of an Opposing Jet from a Hemispherical Nose
Online Contents | 1995
|Axisymmetric Oscillations of an Opposing Jet from a hemispherical Nose
British Library Conference Proceedings | 1994
|