A high pressure transverse air jet is injected into a Mach 5 supersonic model inlet to induce inlet unstart. Planar laser Rayleigh scattering from condensed CO2 particles is used to visualize flow dynamics during the unstart process, while in some cases, wall pressure traces are simultaneously recorded. Boundary layer separation triggered by downstream surface pressure rise is found to precede the formation of a shock system, instantly followed by inlet unstart. Studies conducted over a range of initial inlet flow conditions reveal that the presence of turbulent wall boundary layers affects the unstart dynamics. It is found that relatively thick turbulent boundary layers facilitate faster inlet unstart, when compared to thin, laminar boundary layers.
|Publication status||Published - 2011 Jan 1|
|Event||7th International Symposium on Turbulence and Shear Flow Phenomena, TSFP 2011 - Ottawa, Canada|
Duration: 2011 Jul 28 → 2011 Jul 31
|Conference||7th International Symposium on Turbulence and Shear Flow Phenomena, TSFP 2011|
|Period||11/7/28 → 11/7/31|
ASJC Scopus subject areas
- Fluid Flow and Transfer Processes