Numerical Simulation of Axisymmetric Base Flow on Tactical Missiles with Propulsive Jet

摘要

The axisymmetric Lockheed Viscous Implicit Solver (LVIS) Navier-Stokes computer code is modified to incorporate the capability for computing the flow in the base region of a tactical missile with propulsive jet. Modifications include generalization of the computational space to accommodate the geometry of the base and implementation of two turbulence models of the two-equation type (l-epsilon and k-W). Computer runs are made with both turbulence models. The results of these computations are similar, but some differences are observed in the recirculating near-wake flow and in the shear layers that separate it from the high-speed streams of the propulsive jet and of the external flow. These differences are attributed to the greater eddy viscosity predicted by the k-epsilon model. (Author)