Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
NUMERICAL SIMULATION OF IMPINGING SHOCK WAVE / BOUNDARY LAYER INTERACTION USING MACCORMACK TECHNIQUE
Submission Author:
Ana Maria Pereira Lara , SP , Brazil
Co-Authors:
Ana Maria Pereira Lara, Tiago Rolim
Presenter: Ana Maria Pereira Lara
doi://10.26678/ABCM.COBEM2021.COB2021-0181
Abstract
The objective of this work was to numerically study the shock wave/boundary layer interaction and boundary layer separation caused by impinging shock waves. It was used the explicit solution of the finite differences scheme of the complete two-dimensional laminar Navier-Stokes equations, without body forces and volumetric heating. Also, the following considerations were made for solving the system: calorically perfect gas, Sutherland's law for viscosity, and a constant Prandtl number. The adopted configuration was a supersonic flow with an impinging shock wave on a flat plate. During the tests, it was considered cold and adiabatic wall conditions with the selected free stream Mach numbers of 5, 6, 7 and 8. The impinging shock wave angle varied from 10 to 20 deg. The computer code was developed in MATLAB language using MacCormack’s marching technique. The adopted computational domain was a rectangular structured configuration. From the results, it was noticed that the shock wave could be identified by the jump on the pressure profile, and the highest temperature values were near the flat plate surface. Also, higher pressure and temperature values were encountered for the adiabatic wall case. At the considered Mach number range, at particular angles, the shock wave increase in pressure was high enough to produce boundary layer separation zones, characterized by the presence of a pressure plateau and velocity inversion. Near those zones, it was also observed the flow expansion and further reattachment of the boundary layer.
Keywords
Hypersonic Flow, MacCormack’s technique, Boundary Layer, Shock wave
