P. J. K. Bruce

Experimental Study into the Flow Physics of Three-Dimensional Shock Control Bumps

This paper describes a fundamental experimental study of the flow structure around a single three-dimensional (3D) transonic shock control bump (SCB) mounted on a flat surface in a wind tunnel. Tests have been carried out with a Mach 1.3 normal shock wave located at a number of streamwise positions relative to the SCB. Details of the flow have been studied using the experimental techniques of schlieren photography, surface oil flow visualization, pressure sensitive paint, and laser Doppler anemometry. The results of the work build on the findings of previous researchers and shed new light on the flow physics of 3D SCBs. It is found that spanwise pressure gradients across the SCB ramp and the shape of the SCB sides affect the magnitude and uniformity of flow turning generated by the bump, which can impact on the spanwise propagation of the quasi-two-dimensional (2D) shock structure produced by a 3DSCB. At the bump crest, vortices can form if the pressure on the crest is significantly lower than at either side of the bump. The trajectories of these vortices, which are relatively weak, are strongly influenced by any spanwise pressure gradients across the bump tail. Asignificant difference between 2D and 3D SCBs highlighted by the study is the impact of spanwise pressure gradients on 3D SCB performance. The magnitude of these spanwise pressure gradients is determined largely by SCB geometry and shock position. Copyright

On the Formation Mechanisms of Artificially Generated High Reynolds Number Turbulent Boundary Layers

We investigate the evolution of an artificially thick turbulent boundary layer generated by two families of small obstacles (divided into uniform and non-uniform wall normal distributions of blockage). One- and two-point velocity measurements using constant temperature anemometry show that the canonical behaviour of a boundary layer is recovered after an adaptation region downstream of the trips presenting

Experimental and numerical study of oscillating transonic shock waves in ducts

150~\%

Experimental measurement of wall shear stress in strongly disrupted flows

150% higher momentum thickness (or equivalently, Reynolds number) than the natural case for the same downstream distance (

The triple decomposition of a fluctuating velocity field in a multiscale flow

x\approx 3\,

Coherent structures shed by multiscale cut-in trailing edge serrations on lifting wings

x≈3m). The effect of the degree of immersion of the trips for