Research on Aeroheating of Hypersonic Reentry Vehicle Base Flow Fields

2017 International Conference on Advanced Technologies in Design, Mechanical and Aeronautical Engineering

工业技术;机械制造;航空航天工程

Xuguo, Qin^1 ; Yongtao, Shui^1 ; Yonghai, Wang^1 ; Gang, Chen^1 ; Qiang, Li^1

Beijing Institute of Space Long March Vehicle, Beijing, China^1

关键词: Aero-heating;    Base pressure;    Compressible Navier-Stokes equations;    Heating distributions;    Hypersonic re-entry;    K-Omega turbulence model;    Re-entry vehicles;    Thermal Protection System;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/234/1/012011/pdf
DOI  :  10.1088/1757-899X/234/1/012011

来源: IOP

【 摘 要 】

The structure of the base flow of a hypersonic reentry vehicle and the resulting base pressure and heat transfer have been studied by numerical study. The compressible Navier-Stokes equations are solved by the finite-volume method. SST k-ω turbulence model is used, and comparisons are made with flight test. Attention was focused on assessing the effects of angle of attack and Mach number. It was found that angle of attack can significantly alter the wake flow structure and reentry vehicle base pressure and heating distributions. The results of the simulation may provide a theoretical basis for the design of the thermal protection system of hypersonic reentry vehicles.