Turbulent boundary layer and heat transfer over an aerodynamic body of revolution: Insights into flow structure and thermal interaction

This research endeavors to analyze the turbulent boundary layer characteristics influenced by thermal interactions surrounding a pear-shaped body of revolution, modeled through a mathematical function that closely aligns with contemporary high-speed aerodynamic vehicles. The distinctive geometry of this body is marked by a sharp leading edge coupled with pronounced curvature along the flow's longitudinal axis. A comprehensive assessment of various surface sections was conducted to elucidate the impact of the flow field. The principal aim of this study is to perform an in-depth flow analysis across these surface sections, concentrating on the evaluation of mean and fluctuating velocity components, temperature distribution, pressure distribution, wall skin-friction, local Nusselt numbers, turbulent shear stresses, and turbulent fluxes, as well as the identification of flow separation and recirculation zones. The analysis is grounded in the Reynolds-averaged Navier–Stokes (RANS) framework, employing the k-ω shear stress transport (SST) model, recognized for its reliability in adverse pressure gradient conditions. A weakly compressible flow model is adopted, characterized by a Mach number of less than 0.3 and a Reynolds number of Re = 2.26 × 106, based on the length of the body of revolution. The boundary layer mesh is meticulously constructed with 315020 elements and 20 prism layers, incorporating a stretching factor of 1.2 and a thickness adjustment factor of 0.0084 to ensure an adequate resolution of the wall effects. This study aspires to quantify the thermal interaction processes prevalent in aerodynamic vehicles, ultimately contributing to enhanced design efficiency and optimized performance within a purely mathematical framework.