In:
Advances in Aerodynamics, Springer Science and Business Media LLC, Vol. 3, No. 1 ( 2021-12)
Abstract:
Understanding the generation mechanism of the heat flux is essential for the design of hypersonic vehicles. We proposed a novel formula to decompose the heat flux coefficient into the contributions of different terms by integrating the conservative equation of the total energy. The reliability of the formula is well demonstrated by the direct numerical simulation results of a hypersonic transitional boundary layer. Through this formula, the exact process of the energy transport in the boundary layer can be explained and the dominant contributors to the heat flux can be explored, which are beneficial for the prediction of the heat and design of the thermal protection devices.
Type of Medium:
Online Resource
ISSN:
2524-6992
DOI:
10.1186/s42774-021-00081-y
Language:
English
Publisher:
Springer Science and Business Media LLC
Publication Date:
2021
detail.hit.zdb_id:
2960941-0
