Effect of Mass Transfer on Aeroheating in Hypersonic Chemically Reacting Boundary Layers

[摘要] Heat flux characterization of high-enthalpy boundary layer flows is key to optimize the performance and design of Thermal Protection System of next generation aerospace vehicles [1]. At atmospheric entry hypersonic speeds, ablation as well as surface catalycity impact boundary layer aeroheating. Out-gassing occurring from an ablative surface in planetary entry environment introduces a rich set of problems in thermodynamic, fluid dynamic, and material pyrolysis. Ablation leads to out-gassing and surface roughness, both of which are known to affect surface heating in hypersonic chemically reacting boundary layers via three main routes: gas blowing into the boundary layer from the wall, changing the surface heat transfer due to wall-flow chemical reactions, and modifying surface roughness via ablative processes.

[发布日期] 2019-11-23

[学科分类] 航空航天科学

[关键词] ABLATIVE MATERIALS;AERODYNAMIC HEAT TRANSFER;ATMOSPHERIC BOUNDARY LAYER;BALDWIN-LOMAX TURBULENCE MODEL;BOUNDARY LAYER FLOW;ENTHALPY;HEAT FLUX;HEAT TRANSFER;HYPERSONIC BOUNDARY LAYER;LAMINAR BOUNDARY LAYER;MECHANICAL PROPERTIES;PRESSURE DISTRIBUTION;PYROLYSIS;STANTON NUMBER;SURFACE ROUGHNESS;THERMODYNAMIC PROPERTIES;TURBULENT FLOW;WALL FLOW