Heat reduction and drag mitigation are critical issues in the design of hypersonic vehicles. While existing research has demonstrated that flow control technologies such as spike, aerodisk, and opposing jet technologies can significantly reduce the aerodynamic drag and heat on the nose of hypersonic vehicles in continuum flow fields [1], the performance of these technologies in rarefied flow fields remains underexplored. This study employs the Implicit Multiscale Discrete Velocity Method [2] to systematically investigate the heat and drag reduction effects of a spike-aerodisk-opposing jet configuration in hypersonic rarefied environments. The study examines the effects of flight altitude, Mach number, angle of attack, and the opposing-jet pressure ratio on the heat and drag reduction performance of the configuration. Through comparative analysis of different cases, the following conclusions are drawn: (1) Compared to the spike-aerodisk structure alone, the spike-aerodisk-opposing jet configuration exhibits more significant heat and drag reduction effects; (2) As flight altitude increases, the rarefaction of the gas increases, leading to significant changes in the flow field structure and a gradual weakening of the drag reduction effect of the configuration; (3) The heat and drag reduction effects also change with increasing Mach number; (4) The configuration achieves the best heat and drag reduction effects at an angle of attack of 0°; (5) The heat and drag reduction effects gradually enhance with increasing the opposing-jet pressure ratio.

Heat and drag reduction,Flow control technologies,Hypersonic rarefied environments,Implicit Multiscale Discrete Velocity Method,Spike-aerodisk-opposing jet configuration