Abstract
Instantaneous velocity measurements are necessary to improve the understanding of hypersonic turbulence and shock/turbulent boundary-layer interactions (STBLI). Such measurements are needed to improve the computational fluid dynamic codes required to reduce the developmental risks of new hypersonic systems. Particle image velocimetry (PIV) has been previously used in small-scale experimental facilities to provide global measurements of velocity fluctuations and Reynolds stresses in hypersonic turbulent boundary layers. However, PIV measurements in large-scale test & evaluation hypersonic facilities such as Tunnel 9 are challenging due to the facility scale, reduced test time, and seeding requirements. Based on an extensive literature review, a PIV development strategy has been developed for Tunnel 9. Using 0.25 micron liquid droplets injected at the wall, Stokes numbers of 0.4 and 0.02 are predicted upstream and downstream of the STBLI region produced by a 33-deg flare at Mach 10 for a free-stream Reynolds number of /ft. PIV development work will begin in the Mach 3 Calibration Laboratory before being transferred to Tunnel 9 for PIV measurements on a large scale hollow-cylinder-flare test article. Schlieren images obtained in the new Mach 3 Calibration Lab indicate that an 11 mm thick turbulent boundary layer can be obtained without tripping.
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