An Analysis of Face Gradient Reconstruction Schemes for the Simulation of Aerospace Flows

Author(s)

Oliveira, Frederico Bolsoni ; Azevedo, Joao Luiz F.

• Document type: Journal article
• Source: AIAA SCITECH 2024 FORUM; v. N/A, p. 14-pg., 2024-01-01.

Abstract

An analysis of three distinct numerical schemes for performing face-centered property gradient reconstructions is made in the context of a cell-centered, finite volume formulation. The steady-state dynamics of the fluid flow are computed by solving the compressible Reynolds-averaged Navier-Stokes equations, coupled with the negative Spalart-Allmaras turbulence model. The resulting system of conservation laws is discretized using a second-order, flux-difference splitting method in a total variation diminishing formulation. Two different test cases are considered. The first is the two-dimensional, subsonic, NASA high lift common research model multielement airfoil. The second one is the three-dimensional bump-in-channel. Comparisons are made with other numerical experiments available in the literature. Although all three schemes are capable of achieving similar results, the simplest scheme displays poor convergence properties and even unstable behavior under certain conditions, making it unsuitable for applications in which algorithm robustness is required. (AU)

• FAPESP's process: 13/07375-0 - CeMEAI - Center for Mathematical Sciences Applied to Industry
• Grantee: Francisco Louzada Neto
• Support Opportunities: Research Grants - Research, Innovation and Dissemination Centers - RIDC
• FAPESP's process: 21/00147-8 - A study of limiter functions for high order formulations for compressible flows
• Grantee: Frederico Bolsoni Oliveira
• Support Opportunities: Scholarships in Brazil - Doctorate