Research On Calculation Method Of Hypersonic Pulsating Pressure

In recent years,the field of hypersonic is the focus of aerospace development.Hypersonic flight in the atmosphere is faced with a very harsh load environment,high pressure static load brought by high speed puts forward higher requirements for the aircraft structure,and serious aerodynamic heat and noise problems seriously affect the life of the aircraft structure and the safety of facilities inside the aircraft.This paper will mainly discuss the problem of hypersonic aerodynamic noise.Through previous experiments and theoretical verification and analysis,the formation mechanism and development law of pulsating pressure have been reasonably explained.However,experimental research consumes too much time and energy,which is only suitable for verification calculation and not suitable for engineering application.Therefore,in order to predict the pulsating pressure more efficiently,it is feasible to develop the numerical simulation technology of hypersonic flow field by computer.This paper discusses the formation and development mechanism of pulsating pressure and the corresponding prediction methods,and selects a simple model for calculation verification.Then use hypersonic solver FASTRAN,suitable for wall flow around the S-A single equation turbulent model,analyzed the hypersonic aerodynamic load distribution of the flow field,analyses the form of the fluctuating pressure,direct simulation of boundary layer is given in the difficulty of the fluctuating pressure distribution,so as to set up A simple two-dimensional pointed cone model,using the same numerical analysis method,within the scope of the coming flow Mach number 5 ~ 10,altitude ten thousand meters,when the Angle of 0 degree of some state simulation,get the hypersonic flight conditions the pressure distribution inside the boundary layer,extract the time domain signal of the fluctuating pressure,The distribution of the pulsating pressure level in the hypersonic boundary layer is obtained,and the power spectrum is analyzed and studied by using the Fourier transform function,and the law of its change with the change of the Mach number is verified with the theoretical analysis results.In this paper,a complete method of analyzing hypersonic pulsating pressure using the existing numerical analysis method is established in order to provide more accurate pulsating pressure distribution rules for the acoustic fatigue structure analysis of hypersonic aircraft.