Study of shock turbulent boundary layer interaction in high speed air intake
- Phase II
- Funding Agency: Indian Space Research Organisation
- Project Summary: The flow field generated by the interaction of shock waves with boundary
layers inside a high-speed intake can significantly degrade the performance of the intake and the
quality of flow entering the combustor. Specifically, the interaction of the cowl shock may be
critical in the intake configuration that is of interest to the Air-breathing propulsion project
group at VSSC, ISRO. In the earlier project supported by the STC (Study of shock-turbulent
boundary layer interaction in high-speed air intake, April 2007 - April 2009), the
two-dimensional flow field was analysed using in-house computational fluid dynamic tools. The
actual flow field generated by the cowl-shock interaction is more complex than predicted by
two-dimensional analysis. The focus of the work is to study the three-dimensional effects,
specifically in the vicinity of the side-walls and corners of the inlet duct. A 3D version of the
in-house CFD code is used in the simulations.
- Total Project outlay: Rs. 20.4 lakhs
- Duration and year of initiation: Three years. 2009.