Hypersonic Boundary-Layer Disturbances on a Cooled, Slender Cone at Mach 6

Abstract

This paper presents an experimental study of the effect of wall cooling on the boundary-layer structures of a sharp-nosed, 5° half-angle cone in Mach 6 flow. An experimental methodology was developed that allowed quantitative measurements of second-mode disturbance growth over a range of wall-temperature ratios from [Formula: see text] without modifying the freestream disturbance environment. The cooling system comprised probe cooling, liquid nitrogen injection, and thermal insulation. The model temperature was monitored before each run, with thermocouples mounted at the base and nosetip piece agreeing within 3.3 K. Calibrated schlieren provided global and time-resolved measurements of the boundary-layer features at a freestream unit Reynolds number of [Formula: see text]. An increase in wall-cooling level was associated with a shrinking of the boundary layer and a lowering of wavepacket structure angle at the wall. Despite some outlying results, an overall trend of increasing disturbance frequency with decreasing surface temperature was observed; additionally, cooling increased the spectral amplitude and growth rate of second-mode disturbances, pushing the point of saturation upstream.

Time-resolved wave packet development in highly cooled hypersonic boundary layers

“…This section shows both averaged and time-resolved spectral content generated from schlieren and FLDI diagnostics. To process schlieren data, the boundary layer height was measured from reference-subtracted images using a Sobel filter as in Paquin, Skinner & Laurence (2023b), and the average for Shot 2988 was δ = 0.95 ± 0.04 mm. Wavelet transforms were utilized to identify wave packets in individual images, as discussed by Shumway & Laurence (2015).…”