Effect of Mass Transfer on Aeroheating in Hypersonic Chemically Reacting Boundary LayersHeat 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.
Document ID
20190033884
Acquisition Source
Ames Research Center
Document Type
Poster
Authors
Karimi, Mona (Science and Technology Corp. Moffett Field, CA, United States)
Schulz, Joseph C. (Analytical Mechanics Associates, Inc. Moffett Field, CA, United States)
Mansour, Nagi N. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
December 12, 2019
Publication Date
November 23, 2019
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
ARC-E-DAA-TN76132
Meeting Information
Meeting: American Physical Society's Division of Fluid Dynamics Annual Meeting