Aerodynamic Wedge Probe for Mach Number Measurement in Hypersonic Flows

The objective of this work is to develop the Aerodynamic Wedge Probe (AWP) to measure Mach number in high-temperature hypersonic flows. The first phase of this effort includes a survey of the current state-of-the-art for Mach number measurement in hypersonic flows to ensure the AWP is the appropriate technology to further develop. The second phase of this effort starts with the AWP final design and manufacture, which will be completed in the first half of the Phase II effort. The probe will then be installed in the Aerodynamic and Propulsion Test Unit (APTU) at AEDC where operation will be validated. The modular probe design will be easily maintained and readily adaptable to other test facilities. This leads into the final phase of this work, implementation into other test tunnels, both commercial and government.