Turbulent Shock-Wave/Boundary-Layer Interactions Without Sidewall Effects at Mach 2.5, 3.0, and 3.5 — PIV Measurements From 2025 Test Entry

The High-Mach Validation Experiments (HMVE) campaign was initiated as a follow-on to shock-wave/boundary-layer interaction (SWBLI) experiments previously completed in the NASA GRC 225 cm2 Wind Tunnel at a freestream Mach number of 2.5. Data were collected at Mach 3.0 and 3.5 freestream conditions using the same set of three angles for the conical shock generators in the axisymmetric test section. Select cases from Mach 2.5 testing were also duplicated to verify repeatability. Particle image velocimetry (PIV) measurements were applied to collect large ensembles of velocity data which were stitched together to form a quasi-continuous view of the mean and turbulent flowfield behavior. Densely-spaced wall pressure measurements were concurrently acquired to supplement the flowfield information from PIV. The primary purpose of this report is to summarize the data obtained in this entry and assess the quality and repeatability relative to previous entries. Herein, velocity data is visualized component-by-component in contour plot form to visually assess the ability of the PIV technique to capture detailed flow features. Shock-fitting is used to quantify and correct for small displacements in the shock generator tip which occur due to the long cantilevered support. Since the novelty of this entry comes from the addition of new test cases at reduced Reynolds number, results are presented in a fashion which highlights trends in the flowfield behavior with variation in that parameter. Slices at select streamwise stations are extracted and compared quantitatively across test conditions to identify trends. Data files containing wall-normal profiles of each measured quantity at spacing which matches the companion probe measurements are attached to this report for wider use in comparisons.