Simulation and Optimization of Supersonic Drag Characteristics of Blunt Cone Ascender

doi:10.16182/j.issn1004731x.joss.20-0169

Abstract

Abstract: Reducing shock drag is an important objective of the aerodynamic optimization of Mars ascenders. The CFD(Computational Fluid Dynamics) method is used to study the supersonic drag characteristics of a typical blunt cone ascender. Under the design constraints of slenderness ratio of 0.42, 13 groups busbar shape set of zero-lift drag are compared, and the longitudinal static and dynamic stability are discussed. The research results show that, under the design constraints, the blunt shape with large bulbous and a gently sloped conical surface has low drag characteristics. The reason is that, after passing through the bulbous, the supersonic airflow is continuously expanded and depressurized, and are formed a small area of high pressure at the bulbous nose and a large area of low pressure at the cone surface, which reduce the overall drag. Moreover, the shape of blunt cone has higher static stability and critical dynamic stability.

Key words: Mars Ascent Vehicle (MAV), blunt cone, aerodynamic drag, aerodynamic stability, Computational Fluid Dynamics (CFD)

CLC Number:

TP391.9

Liu Xiazhen, Yuan Wu, Li Qi, Zhao Rui, Zhang Jian, Lu Zhonghua. Simulation and Optimization of Supersonic Drag Characteristics of Blunt Cone Ascender[J]. Journal of System Simulation, 2021, 33(7): 1582-1590.

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