Study of Shock Turbulent boundary layer interaction in high speed air intake
- Funding Agency: Indian Space Research Organisation
- Project Summary: The flow interaction generated by the impingement of an oblique shock on a
turbulent boundary layer will be investigated computationally. The flow field proposed to be
studied is the impingement and reflection of the cowl lip shock in the intake of scramjet engine
configuration of interest to the Air Breathing Propulsion Project at VSSC/ISRO. In-house CFD
codes based on state of the art Reynolds averaged turbulence models will be employed to predict
pressure, heat transfer and flow separation near the shock-impingement location. The
computations will be validated against a well-documented experimental investigation of a
simplified geometry. Inaccuracies in the existing turbulence models often limit the predictive
capability of the CFD codes. Advanced models being developed at IIT Bombay will
therefore be used to improve prediction.
- Total Project outlay: Rs. 16.68 lakhs
- Duration and year of initiation: Three years. 2007.