Numerical Simulation of the Muzzle Flowfield of Embedded Aircraft Gun

Abstract

The muzzle flow of aircraft gun is significantly influenced by the flight speed. Based on the Naiver-Stokes equation and k-epsilon model, the Roe Flux Differencing Scheme was used to simulate the muzzle flowfield of embedded aircraft gun in four different states, viz. inflow velocity of 0, 1.25, 1.5 and 2.5Ma. The structures of the muzzle flowfield were shown clearly, including the interaction process between the muzzle flow and supersonic inflow. The structure features were discussed in detail by comparing the parameters in the static and supersonic flight state. Furthermore, the influence of inflow velocity on the muzzle blast intensity was analyzed.