Abstract:
Complex unsteady flow characteristics and flow-field structures occur therein high speed flow past cavities, such as waves, vortex, and shear-layer. Therefore, it is a hotspot and typical flow structure within aeronautics and astronautics research. Some characteristics are very important in the research such as the cavity test model design, the free-stream Mach number for simulation methods, the selection on boundary-layer thickness, and the differences between computational and experimental results. In consideration of the parameters selection and design method of cavities, the front plate tip configuration and angle are changed on the basis of the analysis on the influence of the front plate tip configuration on the flow characteristics and thickness of the boundary-layer. Parameters selection and design scheme for the determination of a typical plate-cavity model (C201) are presented, with the front plate tip angle of 5°. The parameters selection and design scheme for the C201 cavity model are validated by theoretical analysis, numerical simulation, and wind tunnel test. The basic experimental data about the flow and aeroacoustics characteristics of the C201 cavity model are obtained at Mach numbers of 0.6, 0.9, 1.5, and 2.0. A comprehensive analysis of the surface oil-flow, flow field structure, and pressure within the cavity is presented. Detailed investigations are conducted for the aeroacoustics characteristics and influence law of
Ma and angle of attack on the flow in the cavity. The experimental results can be used for the validation of numerical simulation method and controlling method construction for cavity noise, and also can provide basic data to study noise generation mechanism.