Eventos Anais de eventos
COBEM 2023
27th International Congress of Mechanical Engineering
Preliminary aerodynamics analysis of a three-dimensional bump at subsonic and supersonic flow
Submission Author:
John J Vaca-Rios , SP
Co-Authors:
John J Vaca-Rios, Hernán Cerón-Muñoz
Presenter: John J Vaca-Rios
doi://10.26678/ABCM.COBEM2023.COB2023-0382
Abstract
A three-dimensional compression surface (bump) is used in the inlet system of an aircraft engine to compress the incoming airflow and reduce the boundary layer that is built up over the fuselage. In this paper, both the subsonic and supersonic flow patterns over a bump are studied numerically. The bump is modeled using the Stream Tracing Technique, and it is located on a long flat plate to simulate a typical forebody flow. A three-dimensional structured mesh with eight blocks is generated by using ICEM, a meshing Computational Fluid Dynamics (CFD) software. The Reynolds Averaged Navier-Stokes equations are solved using the ANSYS Fluent code with the turbulence model k-e. The density-based method with the implicit scheme is used for both the supersonic and subsonic cases. The grid sensitivity tests are performed by using bias and grid refinements in the block edges, perpendicular to the walls, and varying the number of elements from 0.5 to 8 million. The results proved that the current bump on supersonic conditions efficiently diverts the boundary layer. In the aerodynamics analysis of the bump flow field, it was found that the spanwise pressure gradient on the bump has a corresponding relationship with the diversion of the boundary layer. The supersonic flight conditions presented a decrease in the total pressure recovery in comparison with the subsonic ones due to the total pressure losses caused by the thickening of the boundary layer, the supersonic flow compression from the shock wave formation, and the existence of shock boundary layer interaction (SBLI) in the supersonic flight conditions. It may be concluded that, due to its acceptable aerodynamic performance, the current bump is an appropriate candidate for integration into a forebody in order to carry out a future aerodynamic analysis of an inlet system.
Keywords
Bump, diversion, shock boundary layer interaction, Computational fluid dynamics (CFD)
