Nonintrusive Diagnostics for Off-Body Measurements in Flight Experiments

ABSTRACT: Developing the quick strike capability of the Air Force requires hypersonic testing using advanced instrumentation to determine key aerodynamic parameters. A novel method for stand-off measurement of gas velocity is proposed. The method should operate over a wide dynamic range, from still air to hypersonic velocities. The method is non-contacting, precise, and spatially-resolved. It does not require seeding the gas, so it is appropriate for large scale wind tunnel measurements and test flights. The Phase I research will (1) demonstrate that the method can be used even in thermal plasmas; (2) identifiy the best components for operating from a hypesonic test platform such as HIFiRE, and (3) determine the size, weight, power and performance characteristics expected for a fully-engineered system. The Phase II research would lead to a prototype system for measurements in wind tunnels or in test flights. BENEFIT: A successful Phase I and Phase II program will lead to specialized test instrumentation for wind tunnels and flight tests. The instrument will be capable of measuring gas flow velocity with high accuracy and precision. The same instrument could be used over a wide range of facilities, including sonic, transonic, supersonic, and hypersonic wind tunnels as well as flight tests on aircraft and rockets.