Complex Spray Flow Field Numerical Simulation And Applied Research

Based on 3-D TLA. Navier - Stokes equations, a finite difference method is developed. A2nd order TVD scheme is used in this method to capture the shock wave more clearly, and two-equation k - ε turbulence model is used to solve the complicated supersonic turbulence flow fields.This method is used to simulate air-air missile plume flows, multi-stage rocket stage-separation flow fields , lateral jet interacting flow fields and flow fields of shock wave diffraction a crack.Because air-air missile plume may endanger fighter security, a detailed numerical investigation of the plume flows of air-air missile has been performed for different condition in this thesis. The flow structures for different altitude and different combustor pressure are compared. A formula is obtained by analyzing CFD data. The result can be used as he foundation to evaluate the edge of pkime flows.A design of stage-separation of multi-stage rocket is discussed. A detailed numerical investigation of the interaction between an engine-jet and the supersonic external flow has been performed for several models. The flow structures for different models of die design are compared, the results show die model with inducing holes is better. The drag on the aft body changed nonlinearly with different separation distance. The result can provide basis for the design of the stage separation partA detailed numerical simulation of a lateral jet interacting with a hypersonic cross flow was performed . The influence of lateral jet pressure ratio and attack angle is performed and numerical simulation results are compared with experimental results. The result shows front separation region enlarges with the increase of jet pressure ratio on the same attack angle and enlarges with the increase of attack angle on the same lateral jet pressure ratio. The result has guiding significance to experimental research and engfaeering application.A detailed numerical investigation of an unsteady flow fields of shock wave diffraction over a crack has been performed for different incident. A set of unsteady flow structures is obtained clearly. The flow structures are compared for different crack, the result predicts they verifies with different crack depth. Higher resolution of shock wave and flow fields discontinues are shown in computation results.