An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle
Source abstract
Abstract
Currently, aerothermal research into scramjet-propelled vehicles characterized by a wedge-shaped section is relatively sparse. Based on the Mach number, grid strategy, and numerical method, an effective simulation scheme for predicting the aerodynamic heat of a scramjet-propelled vehicle during flight is proposed in this paper. At different Mach numbers, the appropriate grid strategy and numerical method were determined by validation tests. Two-dimensional external flow field models based on wedge sections were established and, unlike in blunt bodies, the tests showed that at the high supersonic stage, the ideal cell Reynolds number should be no larger than 16. At the hypersonic stage, the ideal cell Reynolds number and aspect ratio of wall cells near the shock should be no larger than 40, and the AUSM+ flux type performs better than Roe’s FDS flux type at the above stages. The aerothermal prediction indicates that during a flight time of about 34 s, the temperature change reaches about 1913.35 °C, and the maximum average temperature change rate reaches 115 °C/s.
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Research context
OpenAlex topics: Computational Fluid Dynamics and Aerodynamics · Gas Dynamics and Kinetic Theory · Rocket and propulsion systems research
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
Department of Power Engineering and Engineering Thermophysics, College of Mechanical and Power Engineering, Nanjing Tech University, Nanjing 210000, China
Anhui Public Security Education Research Institute (Anhui Public Security College Preparatory Office), Hefei 230000, China
Funding
National Defense Basic Scientific Research Program of China
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