The Goertler instability of a hypersonic boundary layer A and its influence on the wall heat transfer are experimentally ana-2 lyzed. Measurements, made in a wind tunnel by means of a p computerized infrared (IR) imaging system, refer to the flow over 51 two-dimensional concave walls. Wall temperature maps (that are a interpreted as surface flow visualizations) and spanwise heat transfer 6-fluctuations are presented. Measured vortices wavelengths are corre-0 lated to non-dimensional parameters and compared with numerical 0' predictions from the literature.

The present paper deals with an experimental investigation carried out to study some aspects of shock/boundarylayer interaction in nominally two-dimensional hypersonic wedge flow, i.e., over flat plate/ramp configurations. These flow conditions are two dimensional only geometrically because some spanwise periodic variations of the heat flux over the ramp in the reattaching flow region are observed. The measurements, basically made by means of a computerized infrared (IR) imaging system, have been performed in a blowdown wind tunnel at Mach number equal to 7.14 and unit Reynolds number ranging from 7.6 X 10 6 to 24 x 10 6 /m. The influence of the leading-edge shape (bluntness and geometry), flat plate length, and ramp angle on the separation region, average heat transfer at reattachment, and wavelength of the heat transfer variations has been analyzed. IR results are compared to other experimental data as well as to semiempirical correlations for the heat flux peak.

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