Oblique shock

About: Oblique shock is a research topic. Over the lifetime, 6551 publications have been published within this topic receiving 119823 citations.

Control of an Oblique Shock/Boundary-Layer Interaction with Aeroelastic Mesoflaps

Abstract: Aeroelastic mesoe aps for recirculating transpiration have been investigated in an effort to control shock/boundary-layer interactions (SBLIs) through passive cavity recirculation. The mesoe ap concept utilizes a matrix of small e apscovering an enclosed cavity that aredesigned to undergo local aeroelasticdee ection to achieve proper mass bleed or injection when subjected to gasdynamic pressure loading. Experiments were performed to investigate the applicability of the mesoe ap concept for oblique shock interaction by employing shadowgraph e ow visualizations, surface pressure measurements, and mean and e uctuating velocity measurements, along the spanwise midplane of the shock intersection. The experiments were conducted in a Mach 2.41 supersonic wind tunnel operating at a unit Reynolds number of 57 £106 mi1. With the thickest mesoe ap arrays in place, the leading shock formed at the location of the e rst e ap and the boundary-layer thickness at shock impingement was greaterduetoe owinjectionthroughtheupstreame aps.However,thethinnestmesoe aparraysyielded asomewhat reduced boundary-layer thickness downstream of the interaction as a result of the tangential bleeding by the last e aps. Stagnation pressure proe les for the thinnest arrays also showed improved recovery downstream of the SBLI as compared to thesolid-wall case. However, furtherstudy isneeded to investigate three-dimensional effectsand to determine whether this control strategy provides signie cant performance improvements for e ow conditions more consistent with actual inlets.

Boundary Disturbances in High‐Explosive Shock Tubes

Abstract: High‐velocity disturbances are observed to propagate along the walls of a high‐explosive operated shock tube in advance of the plane shock. Experiments are presented which determine the dependence of the geometry, energy, and velocity of the disturbance on such variables as the gas contained in the shock tube, the shock strength, and the roughness and composition of the supporting boundary. A model is constructed to explain the flow within the disturbance. Arguments are presented which show the disturbance to result from radiation originating in the luminous plane shock.

Experiments on the Interaction of a Fast-Moving Shock with an Elastic Panel

Abstract: Experiments on the interaction of a fast-moving oblique shock with an elastic panel in turbulent supersonic flow at Mach numbers of 3 and 4 were conducted to enhance the understanding of coupled flow–structure phenomena and for the validation of coupled simulations. A complex and challenging experimental setup allowed achieving remarkable shock motion, changing the impingement point within a few milliseconds, to excite high-amplitude oscillations of an elastic panel. The flowfield was analyzed by using high-speed pressure transducers and high-speed schlieren photography. The panel deflection was measured by nonintrusive high-speed capacitive and laser distance sensors. Measurements were also conducted on a rigid panel to be used as reference for the elastic case, and to allow a more detailed analysis of the shock-wave/boundary-layer interaction on the panel, yielding insights into the spatial and temporal distribution of frequencies occurring in the interaction area. Oscillations of the elastic panel with...