Bottom Row The Numerical Simulation Of Compound Rocket Shells Extended Range Devices

In this paper, flow field of bottom exhaust-rocket compound extended range projectile has been numerically simulated. The 2~D axissymmetric Euler equations and implicit finite volume TVD schemes are applied. Because of complex computational field, zonal approaches are applied.The shock reflection and wedge-shaped shock reflection were simulated by implicit finite volume TVD schemes. The Emery problem was simulated and domain decomposition method was applied. The results demonstrate that implicit finite volume TVD schemes have good capability deal with complicated wave reflection and complicated boundary. Finite volume TVD schemes are applied to solution axissymmetric two dimension Euler equations. Free jet flow field of rocket nozzle was simulated and concluded a good result, flow field of nozzle outlet in different position of the cavity of bottom exhaust has been numerically simulated and thrust loss has been studied. It also presents three major factors of causing thrust loss that are the distribution of density, the exhaust velocity and pressure on the section of outlet. Lastly the variational law of thrust loss by different position of nozzle outlet in the bottom exhaust cavity is carried out.The complex flow field induced by the interaction between the supersonic flow around the body and rocket jet of inside bottom exhaust cavity was simulated by implicit finite volume TVD schemes. Domain decomposition method was applied. The Mach number was 2.0 and 2.5, and the attack angle was 0? The variational law of pressure and density were shown along surface of projectile base and thrust loss.Pressure contours, density contours and mach contours are drawn and shown clear flow structure.