Control of shock wave - boundary layer interactions in high speed aerospace vehicles
The interaction of the shock waves with the boundary layers is the basic fluid-dynamics phenomenon that has both fundamental and practical importance.
From the practical standpoint, the interaction of SWBLI can have significant influence on aircraft or rock performance and often leads to extremely undesirable effects, such as drag rise, massive flow separation, shock unsteadiness and high wall heating. It is of interest not only due to its fundamental value but also due to the importance in aeronautical applications. It appears in external and internal aerodynamic flows on wings, rotors as well as turbo-machinery blades. It also present under steady or unsteady (transonic buffeting) conditions.
The goals of this project are:
- to explore the critical question related to dynamic of shock wave/boundary layer interaction by comprehensive literature review
- to carry out a thorough understanding of the relationship between the upstream boundary layer, and the method to suppress or control shock-wave boundary layer interactions
- to develop strategies to mitigate the negative effects such as large pressure and thermal loads which are responsible for damage to aero-structures and thermal protection systems, loss of efficiency of control surfaces
- validated with experimental data set up a guideline for design application purposes all these effects are posing the array of problems to the designer of high speed vehicle.