The effect of tripping devices on a shock wave - boundary layer interaction

Master thesis (2015)

Authors

R. Louman Aerospace Engineering

Contributors

B.W. van Oudheusden Aerodynamics - Aerospace Engineering (mentor)
F.F.J. Schrijer Aerodynamics - Aerospace Engineering (mentor)
R.H.M. Giepman Aerodynamics - Aerospace Engineering (mentor)
G.E. Elsinga Fluid Mechanics - Mechanical, Maritime and Materials Engineering (mentor)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2015 Renee Louman
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Published Date

15-01-2015

Language

English

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Faculty

Aerospace Engineering

Abstract

Shock Wave Boundary Layer Interactions (SWBLIs) occur frequently in supersonic and hypersonic flows and, depending on the strength of the shock wave and the state of the boundary layer, may lead to boundary layer separation. This can result in a multitude of problems, such as an increase in drag, a drop in air intake efficiency and high fatigue loads due to the inherent unsteadiness of the ow phenomenon. Since a turbulent boundary layer has a better capability to withstand the adverse pressure gradient that is inherent to the incident shock wave when compared to a laminar boundary layer, it is beneficial to have a turbulent boundary layer at the interaction. By forcing boundary layer transition only a short distance upstream of the interaction, the capability of the boundary layer to remain attached is increased while retaining the low skin friction coefficient of a laminar boundary layer for as long as possible.

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