背部进气布局飞机前机身模拟器设计方法研究与评估  

Research and Evaluation of Design Method of Forebody Simulator Based on Dorsal Intake Layout Aircraft

作　　者：王学峰 钟易成[1] WANG Xuefeng;ZHONG Yicheng(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》2024年第5期82-86,134,共6页Machine Building & Automation

摘　　要：为满足背部进气布局飞机的前机身-进气道-发动机自由射流试验的需求,设计前机身模拟器以模拟原始前机身对进气道内流场的影响。根据背部进气布局飞机的流动特点,设计两类前机身模拟器,在自由射流试验舱内模拟飞行高度10 km、飞行速度0.7Ma的3种飞行姿态的流场。通过对比子午面和进气道出口流场以及进气道出口平均参数,证明所设计的前机身模拟器可以在射流环境下模拟原始前机身的前机身效应,其中负攻角和侧滑角姿态下的前机身模拟器模拟效果较好,而正攻角姿态下的前机身模拟器模拟效果相对较差。In order to meet the needs of the forebody-intake-engine free-jet test of dorsal intake layout aircraft,the forebody simulator is designed to simulate the effect of the original forebody on the flow field in the intake tract.According to the flow characteristics of the dorsal intake layout aircraft,two types of forebody simulators are designed,and the flow field of three flight attitudes with a flight altitude of 10 km and a flight speed of 0.7 Ma is simulated in the free jet test cell.Comparison of the meridian surface and intake outlet flow fields and the average parameters of intake outlet proves that the designed forebody simulator can simulate the forebody effect of the original forebody in the jet environment,among which,the simulation effect of the forebody simulator under the negative angle of attack and side slip angle attitude is better,while the simulation effect of the forebody simulator under the positive angle of attack attitude is relatively poor.

关 键 词：背部进气布局 前机身模拟器 鼓包进气道 自由射流试验 前机身效应 

分 类 号：V216.8[航空宇航科学与技术—航空宇航推进理论与工程]