摘要
为了建立球面高超声速稀薄流气动热的工程算法,采用直接模拟蒙特卡罗法(DSMC)进行多种工况下的计算,对3种计算驻点气动热的工程算法进行考察,选取具有较高精度的实验数据相关法公式作为驻点热流计算依据,得到球面关于驻点的归一化热流值,分析来流及几何参数变化对归一化热流分布的影响,最后得到球面热流的工程计算公式。该公式克服了桥函数法在球面后半部分计算结果严重偏离DSMC方法预测结果的问题,具有较高的精度。
In order to establish the engineering algorithm for calculating aerodynamic heating of sphere at hypersonic rarefied flow, the Direct Simulation Monte Carlo （DSMC） method is applied at different conditions. Three kinds of engineering methods to calculate heating at the stagnation point are compared and the correlation method of experimental data, which is more accurate than the bridging methods, is chosen. Analysis is made to get the influences of the inflow and geometry parameters over normalized aerodynamic heating, and the engineering algorithm is obtained by the normalization method. The problem of its deviating from the DSMC predictions at the second half of the sphere in bridging methods is solved in this algorithm, which also shows a higher accuracy than bridging methods.
出处
《导弹与航天运载技术》
北大核心
2012年第5期32-38,共7页
Missiles and Space Vehicles
关键词
稀薄流
气动热
DSMC方法
归一化方法
Rarefied flow
Aerodynamic heating
DSMC Method
Normalization method
