基于三维内转式进气道的前体一体化设计  

Integrated Design of Osculating Cone Waverider Forebody Based on Three-dimensional Inward-turning Inlet

作　　者：李铮 袁化成[1] 杨德壮 LI Zheng;YUAN Huacheng;YANG Dezhuang(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2023年第4期60-63,共4页Machine Building & Automation

基　　金：航空科学基金项目(20200012052001)。

摘　　要：提出一种基于气动融合的内转式进气道/吻切锥乘波前体的一体化设计方法。介绍吻切锥乘波前体设计方法并进行仿真验证,提出基于给定内转式进气道的吻切锥前体匹配方法,根据一体化方法进行典型构型设计与数值仿真。仿真结果表明:基于此方法得到的前体/进气道构型在设计状态流量捕获系数达到了0.963,进气道喉道总压恢复系数为0.675。A design method integrating osculating cone waverider forebody with internal-turning inlet based on pneumatic fusion is proposed.The design method of osculating cone waverider forebody is initially introduced and tested throguh simulation,the matching method based on the given internal-turning inlet is put forward and the typical configuration design and numerical simulation are conducted according to the integration design.The simulation results show that the flow capture coefficient of the forebody/inlet configuration obtained based on the proposed method reaches 0.963 and the total pressure recovery coefficient of the inlet throat is 0.675.

关 键 词：飞行器 吻切锥 乘波前体 内转进气道 一体化设计 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]