DETACHED SHOCK WAVES ANALYSIS FEDSM2006-98394

ABSTRACT The work to be presented herein is a Computational Fluid Dynamics investigation of the complex fluid phenomena specifically with regard to the structure of detached shock waves over a moving body. This paper will show a relationship between the geometrical data and the strength and position of the detached shock waves, over moving body. The aim of this paper is to develop a relationship between the Mach number, the geometry and the strength of the detached shock wave. A study was completed on a different number of configurations. Results including contour plots of Mach number, static pressure, and static temperature showed the structure of 2-D detached shock waves in a complex region. A CFD analysis enables one to understand the complex flow structure of the detached shock waves over a body with different configurations. The results will show that for η>1 the detached shock will stand at farther distance than η<1 for the same geometrical shape. Through this computational analysis, a better interpretation of the physical phenomenon of the two dimensional detached shock waves can be achieved and to use this knowledge to achieve a design methodology that will benefit the industrial applications. INTRODUCTION A computational model that illustrates the physics of flow through detached shock waves was developed. The flow is viscous and high speed compressible. In this situation, one should expect oblique shock waves, expansion fans, shock wave interactions, and slip surface generation The results will show a promising achievement, first, to understand the flow structure of a supersonic flow over a blunt body, second, to use this knowledge to interpolate the numerical results in order to achieve a design methodology that will benefit the industrial applications. Results including contour plots of Mach number, static pressure, and static temperature will show the structure of detached shock waves. A CFD analysis enables one to understand the complex flow structure around blunt bodies. Through this computational analysis, a better interpretation of the physical phenomenon of the detached shock waves can be achieved Bow or detached shocks occur where the supersonic body is too blunt to allow the shock to attach to the apex. These shocks are curved and form at 90 degrees to the oncoming flow. The shape and position of the detached shocks are extremely difficult to derive from fluid mechanics relations. Instead, assumptions and approximations are used. The rules governing the distance between the blunt body and the shock are complicated, and are a function of the shape of the blunt body. The distance of the shock standoff from a blunt body has been of interest from the earliest studies of supersonic aerodynamic flow. The distance varies drastically with the temperature for the gas.The development in understanding of the shape and size of a detached shock wave in front of a blunt body is closely linked to the success of computational fluid dynamics simulations and wind tunnel tests COMPUTATIONAL FLUID DYNAMICS ANALYSIS The governing equations are a set of coupled nonlinear, partial differential equations. In order to formulate or approximate a valid solution for these equations they must be solved using computational fluid dynamics techniques. To solve the equations numerically they must be discretized. That is, the continuous control volume equations must be applied to each discrete control volume that is formed by the