Interaction of Hypersonic Boundary-Layer Instability Waves with Axisymmetric Compression and Expansion Corners

摘要

Experiments were carried out in the University of Maryland's HyperTERP hypersonic shock tunnel to investigate the interactions between instability waves within a slender-cone boundary-layer and axisymmetric compression/expansion corners. The test article consisted of a 5° half-angle cone with interchangeable flares of 0° and 15° half-angles. A streamwise array of PCB X32B38 transducers measured the surface pressure fluctuations while a high-speed schlieren system was implemented for flow visualization at frame rates as high as 619 kHz. The compression flare was found to create a region of corner flow separation and promote rapid breakdown of the instability waves upon reattachment. The expansion flare, on the other hand, was observed to have a stabilizing effect on the disturbances, leading to rapid dissipation and a reduction in surface pressure oscillations downstream of the cone/flare junction. The high frame rate employed in this campaign facilitated the use of spectral analysis to examine the spatial development of modal content within the field of view.