English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Tools annual

Global: Zendy Free Plan

Global: Zendy Tools monthly

Global: Zendy Plus monthly

A detailed knowledge of the flow structure interaction in supersonic flows is important for the design of future space transportation systems. Therefore this work was devoted to the investigation of the shock wave boundary layer interaction on an elastic panel. During the wind tunnel experiments the panel deflection was measured with fast non-intrusive displacement sensors. On the flow side pressure, high-speed Schlieren photography and oil-film technique were used. The flow manipulation due to the panel deflection becomes manifest in a deformation of the impinging shock and the separation zone. The panel deflection consists of a constant and a dynamic component. The experimental results are discussed and compared to numerical results.

Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow