Abstract
The fairing is used to protect the aircraft from aerodynamic heat and force at high-speed, while there exists strong shock-vortex interaction during fairing separation. The unsteady shock-vortex interaction is numerically studied based on dynamic unstructured overset grid in this paper, where the N-S equations and 6-DOF equations are couple solved. Due to the blocking effect of fairings and shocks, there is a strong vortex inside the fairings. With the separation of fairings, the vortex is strongly compressed by the shock of fairing. When the shock is very close to fairing, the vortex is forced into the Mach cone of aircraft and enlarges the Mach cone. There exists a strong shock-vortex interaction of shock-vortex compressing, transforming of vortex boundary and vortex-shock compressing during fairing separation.
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