Developing and extension of diagnostic techniques for advancing high speed aerodynamic research

The authors present diagnostic techniques for high-speed turbulent boundary layer studies in Mach 3 and Mach 6 high Reynolds number facilities and flow interactions in the low-density 51-cm hypersonic wind tunnel at Mach 12 and 14. Direct measurement of skin friction and heat transfer on smooth and rough surfaces, electron-beam flow visualization, hot-wire anemometry, flow speeding for laser velocimeter measurements, and unsteady pressure measurements on model surfaces are presented and discussed. Emphasis is placed on combining techniques for more complete characterization of the phenomena being studied.<
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