物體螺旋前進過程之流場分析

Abstract

本文主要探討的是飛彈發射飛離發射套筒後，套筒內部的相關熱流現象。飛彈的發射通常一次會有4個或是8個等複數個飛彈在發射台上依序發射，以期達到更大的破壞力。而飛彈發射後在短暫的時間內飛離套筒，發射時飛彈後端會產生大量的高溫高壓氣體，影響到其餘尚未發射地套筒的準度。本研究利用流體力學輔助軟體Fluent作為計算平台，運用LES紊流模式，解三維暫態Navier-stoke equations，並利用有限容積法(finite-volume)來計算，以ROE法來計算格點間的通量，以及使用2nd-Order Implicit進行暫態的疊代方法，計算飛彈飛離套筒後，套筒內部的流場變化情形。

This study discuss the heat transfer and flow field inside the launch sleeve when the missile is launching and leaving the sleeve. To be more destructive. There are usually 4 or 8 missiles to be launched one by one. The missile leaves the sleeve in a short time, and a high pressured and high temperature gas will be made in the back of the missile, affects those missiles which haven't launched. This study uses the CFD software FLUENT as computing platform, adopts the LES turbulence model to solve the three-dimensional transient Navier-Stokes equations, and the finite volume method is used with ROE scheme applied for the flux between grids. Finally, a 2nd order implicit method is used to calculate the transient state of flow flied inside the sleeve when missile leaves the sleeve.