CAJ | 학술논문

本文介绍了中国科学院高温气体动力学重点实验室在超高速高焓流动模拟技术和试验方法方面取得的研究进展.文章主要包括三部分研究内容:第一部分是关于发展先进的超高速试验模拟技术,包括爆轰驱动高焓激波风洞和爆轰驱动高焓膨胀管.高焓激波风洞产生的超高速气流速度的范围是3.5km/s～6.0km/s,高焓膨胀管能够模拟速度为6.5km/s～10km/s的超高速气流.第二部分介绍高焓激波风洞喷管流场诊断结果,用来检验喷管产生的超高速流场的流场品质及其与飞行条件的差异.第三部分是关于超高速流动的试验方法和数值技术研究,包括高焓流动中真实气体效应对飞行器俯仰力矩变化的影响;热化学反应流动中表面催化效应诱导的气动热变化规律;喷管流场的气流非平衡效应对试验结果可能产生的影响.
본문개소료중국과학원고온기체동역학중점실험실재초고속고함류동모의기술화시험방법방면취득적연구진전.문장주요포괄삼부분연구내용:제일부분시관우발전선진적초고속시험모의기술,포괄폭굉구동고함격파풍동화폭굉구동고함팽창관.고함격파풍동산생적초고속기류속도적범위시3.5km/s～6.0km/s,고함팽창관능구모의속도위6.5km/s～10km/s적초고속기류.제이부분개소고함격파풍동분관류장진단결과,용래검험분관산생적초고속류장적류장품질급기여비행조건적차이.제삼부분시관우초고속류동적시험방법화수치기술연구,포괄고함류동중진실기체효응대비행기부앙력구변화적영향;열화학반응류동중표면최화효응유도적기동열변화규률;분관류장적기류비평형효응대시험결과가능산생적영향.
The research progress on high-enthalpy and hypervelocity flows achieved in the Institute of Mechanics,Chinese Academy of Sciences.is reported in this paper.The paper consists of three main parts:The first part is on the techniques to develop advanced hypervelocity test facilities,in which the detonation-driven shock-reflected tunnel and the detonation-driven shock-expanded tube are introduced.The shock tunnel can be used for generating hypervelocity flows of the Mach number ranging from 10 to 20,and the expansion tube is applicable to the flow generation at the orbital speed of 7-10 km/s.The second part is dedicated to the nozzle flow diagnosis in JF10 shock tunnel to examine the quality of the hypervelocity flows thus created for determining its discrepancies with the corresponding flight conditions.The third part is on experiments and numerical simulations,which include measuring the aerodynamic pitching moment and the heat transfer due to surface catalysis,simulating nozzle flows for evaluating non-equilibrium effects on the possible experiments that will be carried out on the above-mentioned facility.