With Wing Tail Rocket Missile Three-dimensional Flow Around A Complex Flow Field Numerical Simulation Of The Jet Interference

The 3-D complex flowfield of rocket-missile with wings and empennages induced by the interaction between by base jet and the flow around the body has been numerically simulated. The main work is as follows:First, the Gordon-McBride program was developed to make it more friendly and efficient to the users. Also an example for the use of it was given.Then, the Navier-Stokes equations for 2-D axisymmetric compressible turbulent flow were constructed and Phoenics was used to simulate the 2-D axisymmetric compressible turbulent flowfield of rocket jet.Finally, the Navier-Stokes equations for 3-D compressible turbulent flow were constructed and also the standard k-ε equations and standard wall functions were given. Fluent was used to simulate the flowfield of 3-D complex flowfield of rocket-missile with wings and empennages induced by the interaction by base jet and the flow around the body. In order to study the complex flow problem above, numerical simulations were performed under the following kinds of flow conditions: (l)flow of rocket-missile with wings disturbed by supersonic upstream flow. (2)flow of rocket-missile with wings disturbed by supersonic upstream flow with attack angle. (3)flow of rocket-missile with wings disturbed by jet and supersonic upstream flow with attack angle. (4)flow of rocket-missile with wings disturbed by subsonic upstream flow with attack angle. (5)flow of rocket-missile with wings and empennages disturbed by supersonic upstream flow with attack angle. (6)flow of rocket-missile with wings and empennages disturbed by jet and supersonic upstream flow with attack angle. The distinct flowfield structures with shock waves and vortices had been obtained. The simulation results were studied the interaction mechanisms among burning jet flow and upstream flow were demonstrated.