Flow and heat flux features for supersonic flow past aircraft model

Ya. V. Khankhasaeva, V. E. Borisov, A. E. Lutsky, A. V. Severin

Keldysh Institute of Applied Mathematics RAS

Abstract: Numerical simulation of supersonic ($\mathrm{M}_\infty= 2.5$) flow of viscous heat-conducting gas past an aircraft model for various attack angles and wall temperatures was carried out on the basis of an unsteady Reynolds averaged Navier–Stokes equations system (URANS) with Spalart–Allmaras (SA) and Menter’s SST turbulence model as well as with the hybrid IDDES+SA method. Three-dimensional features of the flow and surface heat flux’s dependence on wall temperature were investigated. Base flow’s dependence on the chosen turbulence model was studied. Comparison of simulation results with experimental data was carried out.

Keywords: URANS, SA, SST, IDDES, base flow, isothermal wall, heat flux density.

Received: 14.10.2024
Revised: 20.05.2025
Accepted: 09.06.2025

DOI: 10.20948/mm-2026-01-10