Numerical Simulation of the Impact of Ventral Sting on Supersonic Aerodynamics and Flow Field

摘要

In supersonic or hypersonic air tunnel testing, the model is generally mounted with tail support. In some special cases, however, ventral sting is used. Ventral sting does not only induce shock waves around the support, its wake also modifies the bottom flow distribution and surface pressure coefficient of the model, causing changes in the aerodynamics and flow structure across the model in the form of support interference. In this paper, the circular flow field of a blunt body under supersonic inflow with and without ventral support is simulated by solving the RANS equation with the FVM second-order accuracy Roe scheme, and the possible impact of different ventral support profiles on the aerodynamics and flow field of the model is examined through comparison of the aerodynamics and pressure distribution under different conditions, together with characterization of the flow structure of the model. The result shows that ventral sting has considerable impact on the aerodynamics of the model; different ventral support profiles vary in their amount of interference; and the presence of ventral sting modifies the pressure distribution at the bottom of the model. It is recommended that ventral sting be designed to avoid the induction of detached shock waves and the effect of a significant separated region on the model.