Yujoo KANG, Sang LEE

DOI Number: 10.60853/qa87-wp92

Conference number: HiSST-2024-00170

This study investigates shock-turbulent boundary layer interaction (STBLI) over a 24∘ compression ramp at Mach 2.9 using direct numerical simulation. An in-house code based on a compact finite difference scheme is introduced and validated. Two distinct turbulent kinetic energy hotspots are identified: one near the wall behind the separation point and another in the free shear layer near the reattachment point. A significant factor contributing to the second amplification phenomenon is elucidated, involving the cluster of shocklets near the reattachment point. Analysis of pressure fluctuation power spectral density reveals concentrated high-pressure fluctuation regions near both separation and reattachment points, with distinct low and mid-to-low frequency phenomena observed, particularly near the separation point.

Read the full paper here

In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.