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Numerical Simulation of Lateral Thrusters in Hypersonic Flow Over a Biconic Body

机译：双锥体高超声速横向推进器的数值模拟

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A Navier-Stokes simulation of lateral thrusters on a biconic body in hypersonicflow is presented. Due to simplifications arising from symmetry, cruciform thrusters were considered first. A grid convergence was conducted to evaluate computational accuracy. This was followed by the computation of three different jet exit conditions and an assessment of the flow field changes produced by each. Of particular concern was the possibility of entrapment of streamlines from the jet in a recirculation region upstream of the jet. The final case considered was a single jet thrusting from a biconic body at zero incidence at M = 9.7. These results were compared to experimental surface pressures. A description of the complicated interacting flow fields featuring multiple separation and attachment lines/regions is also presented. Biconic body, Hypersonic flow.

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