Fatmanur Aleyna ÖZCAN, Muhammed Osama BALKHI, Ahmet Selim DURNA

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-429

Shock-wave boundary layer interaction is therefore a spectacle commonly associated with aerospace
devices when a shock wave meets a boundary layer in high-speed flows. In this study, the effect of
different ramp lengths at three different ramp angles of 24º, 33º, and 50º, respectively, at M=2.52 will
be examined. Investigations were performed with a commercial Computational Fluid Dynamics software
based on two different ramp angle geometries with Schlieren images. The results obtained are
compatible with the experimental results. The separation shock’s angle is independent of ramp angle
and length. Separation width increases with ramp angle and length. The separation shock’s strength
increases with ramp angle, however reattachment shock’s strength almost stays constant.

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In Categories: 1.Events, HiSST 2022
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