CAJ | 학술논문

根据进气道内部流动特征,并结合现有工程设计经验和试验结论,提出从进气道喉道段出口截面截断,简化取其超声速扩压段和喉道段与其外部流场统一构造出具有单一性态超声速流动的流场计算域,既缩减了CFD数值模拟的计算规模,又提高数值计算的收敛性.经实例计算分析表明,解算速度和效率大大提高,单个计算工况仅需时不到20 min即可快速完成求解,并可基于数值计算模型提取出进气道捕获流量和最大总压恢复系数等全部主要性能参数,特剐适合于在超声速进气道方案设计阶段用来快速进行性能评估和方案选型,有利于提高设计效率,缩短研制开发周期.
근거진기도내부류동특정,병결합현유공정설계경험화시험결론,제출종진기도후도단출구절면절단,간화취기초성속확압단화후도단여기외부류장통일구조출구유단일성태초성속류동적류장계산역,기축감료CFD수치모의적계산규모,우제고수치계산적수렴성.경실례계산분석표명,해산속도화효솔대대제고,단개계산공황부수시불도20 min즉가쾌속완성구해,병가기우수치계산모형제취출진기도포획류량화최대총압회복계수등전부주요성능삼수,특과괄합우재초성속진기도방안설계계단용래쾌속진행성능평고화방안선형,유리우제고설계효솔,축단연제개발주기.
Based on internal flow characteristics of inlet, and combined with existing engineering design experiences and exper- iment conclusions, a fast computational fluid dynamics(CFD) modeling and computation scheme is presented. It not only simplifies CFD simulation scale, but also improves numerical convergence by constructing a computational domain with supersonic flow, which is formed by unifying supersonic diffuser and external flow field of throat. The results show that computation speed and efficiency are greatly improved. It takes less than 20 min to solve a single case. And all the major performance parameters, including captured mass flow and maximal total pressure recovery coefficient of the inlet, can be easily extracted from computation results. It is espe-cially suitable for fast performance evaluation and scheme selection in design stage, resulting in higher efficiency and faster design cycle.