What is it about?
Oblique shock–boundary layer interactions cause large stagnation pressure losses in high-speed aircraft, hence worsening performance. We test a flexible panel as a simple means to control them. Using experiments and simulations, we find that these interactions can be weakened when the panel is used, leading to improved efficiency.
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Why is it important?
We find that using flexible surfaces can lead to significant reductions in the losses due to oblique shocks. This could be used to improve the performance of supersonic engine inlets.
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This page is a summary of: Oblique Shock Control with Steady Flexible Panels, AIAA Journal, May 2020, American Institute of Aeronautics and Astronautics (AIAA), DOI: 10.2514/1.j058933.
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