In-Flight Visualization of Supersonic Flow Transition Using Infrared Imaging

Infrared visualization was used to obtain information on the state of the boundary layer of a natural laminar flow airfoil in supersonic flight. In addition to the laminar/turbulent transition boundary, the infrared camera was able to detect shock waves and present a time-dependent view of the flow field. Thermal and flow mechanisms on the surface in flight were modeled numerically to aid in the design of the flight experiment and facilitate analysis of recorded infrared footage. A commercially available infrared camera was adapted for airborne use in this application. Readily available infrared technology has the capability to provide detailed visualization of various flow phenomena in subsonic to hypersonic flight regimes.