Measurements on BOLT and Flat-BOLT in Mach-6 Quiet and Conventional Flow

Experiments were performed on 33% scale Boundary Layer Transition (BOLT) and Flat-BOLT models in the Purdue University Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) to characterize the boundary layer under hypersonic quiet flow. For both geometries surface heating measurements were taken using infrared thermography, and high-frequency pressure fluctuations were measured using PCB Piezotronics pressure transducers. Measurements were taken within the boundary layer off-surface on the Flat-BOLT geometry using schlieren. These results are intended for comparison with conventional noise Mach 6 flow wind tunnel experiments and computations which are available on both BOLT and Flat-BOLT geometries.