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

Karimi, Mona ; Schulz, Joseph C ; Mansour, Nagi N

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;   

RP-ID  :  ARC-E-DAA-TN76132

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 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.