Abstract
Interaction of shockwaves with turbulent boundary layer plays an important role in the design and operability of high-speed aerospace vehicles and air-breathing engines. The adverse pressure gradient of the shock is often strong enough to separate the boundary layer. The objective of the present research paper deals with the analysis of hypersonic viscous flows dominated by strong shockwave/boundary-layer interactions (SWBLI) over wing-flap and wing-fuselage junction configurations. The effects of the control surface deflection angle, leading edge shape and viscous interaction parameter on the flow field have been evaluated. Scaling laws for the upstream influence, and peak heating, pressure coefficient, skin friction and aerodynamic coefficients have been established by means of numerical simulations and theoretical considerations. Both linear and non-linear turbulence models are considered during simulation of SWBLI. Tec plot plays a crucial role for interpreting and post-processing CFD data to numerical data for contrasting altogether.
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