Simulation of supersonic flows with shock-boundary layer interactions

• Grant number: 25/08181-1
• Support Opportunities: Scholarships in Brazil - Scientific Initiation
• Start date: August 01, 2025
• End date: July 31, 2026
• Field of knowledge: Engineering - Aerospace Engineering - Aerodynamics
• Principal Investigator: William Roberto Wolf
• Grantee: Sofia Teixeira Escobar Rodrigues
• Host Institution: Faculdade de Engenharia Mecânica (FEM). Universidade Estadual de Campinas (UNICAMP). Campinas , SP, Brazil
• Associated research grant: 21/06448-0 - High-fidelity numerical simulations applied in unsteady aerodynamics, turbulence and aeroacoustics, AP.JP2

Abstract

In this work, the Reynolds-averaged Navier-Stokes (RANS) equations 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. Comparisons of different turbulence models will be performed to assess their impact on the shock-boundary layer interactions (SBLIs) forming in the present cases. This study finds application in the design of supersonic fluid machinery, aircraft control surfaces, besides supersonic inlets. The results obtained will serve as preliminary analyses for the high-fidelity simulations planned in the laboratory. Effects of curvature on pressure gradients will also be investigated, using both the Euler and RANS equations.