Investigation of base flows with hypersonic freestreams

The sensitivity of base flow topology to exit area ratio and pressure ratio is extremely important in the design of high-speed vehicles, especially missiles. Minor changes in pressure ratio and open area ratio can significantly impact the propulsive efficiency of a system and even introduce unwanted asymmetry and unsteadiness. There is very limited information available about such flows with a high supersonic/low hypersonic freestream.

To fill this knowledge gap, these base flows will be experimentally investigated in the University of Manchester High Supersonic wind tunnel. A new model and rig will be built to enable blown model testing and the flow topology will be investigated using non-intrusive measurement techniques. Axisymmetric and asymmetric nozzles can be investigated.

Three-dimensionality can be investigated through the use state-of-the-art flow diagnostic methodologies such as full-surface pressure-sensitive paint (PSP) and off-surface particle image velocimetry (PIV) measurements.