A study of supersonic boundary layers developing under streamwise curvature and pressure gradients

• Grant number: 24/20547-9
• Support Opportunities: Scholarships in Brazil - Doctorate
• Start date: March 01, 2025
• End date: February 28, 2026
• Field of knowledge: Engineering - Aerospace Engineering - Aerodynamics
• Principal Investigator: William Roberto Wolf
• Grantee: Lucas Feitosa de Souza
• Host Institution: Faculdade de Engenharia Mecânica (FEM). Universidade Estadual de Campinas (UNICAMP). Campinas , SP, Brazil
• Associated research grant: 13/08293-7 - CCES - Center for Computational Engineering and Sciences, AP.CEPID

Abstract

In this work, wall-resolved large eddy simulations (LES) will be employed to simulate supersonic boundary layers over canonical streamwise-curved surfaces. Convex and concave surfaces will be investigated leading to favorable and adverse pressure gradients, respectively. Since the flows are supersonic, compression and expansion waves will be generated and, in the former scenario, coalescence to shock waves may occur. The boundary layers will be tripped to enforce turbulence, but the finite length of the investigated geometries may not allow the full development of the turbulent regime, and this is one of the aspects to be investigated. Shock-boundary layer interactions (SBLIs) will also be analyzed for the present cases, where the Rankine-Hugoniot jump relations will be imposed as boundary conditions to generate shock waves. This study finds application in the design of supersonic fluid machinery, aircraft control surfaces, besides supersonic inlets.