摘要
针对吸气式高超声速飞行器推进/气动一体化设计问题,设计了一种以超燃冲压发动机为动力的吸气式高超声速飞行器。以此为约束,开展了弧形前缘和平直前缘前体/进气道一体化方案设计,并采用数值模拟的方法对前体/进气道的典型性能进行了仿真研究。结果表明:弧形前缘前体/进气道一体化设计方案满足指标要求;变强度配波的弧形前缘前体/进气道在设计点状态下各纵向剖面的外压缩波系均与进气道进口保持贴口状态,避免了部分外压缩激波入射到内通道加重热防护负担的问题;与平直前缘相比,一方面弧形前缘前体将使得前缘脱体激波沿展向蜕化,有利于进气道进口气流总压恢复性能的提高,另一方面弧形前缘的前体前缘形状不利于排除进气道进口边界层气流,导致了其进气道喉道和出口截面下壁面更多的低总压堆积区,使得进气道的总压损失进一步增大,因此,弧形前缘对内流性能的影响需要综合评价。
To deal with the integrated design problem of air-breathing hypersonic vehicle,an scramjetpowered air-breathing hypersonic vehicle has been designed,with constraint of this vehicle,a fore-body/inlet integration scheme with radial leading edge is designed and simulated by the way of computing fluid dynamics. The results show that,forebody/inlet integration scheme with radial leading edge satisfied all the performance index at the design condition; the out compression waves system of radial leading edge forebody/inlet with variable strength shock is near with the inlet,which avoid the thermal protection problem which will aggravate the aerodynamic heat; compared with the forebody/inlet integration scheme with straight leading edge,the detached shockwaves of forebody/inlet integration scheme with radial leading edge decayed in span-wise,the entropy layer near the wall became thin,which was propitious to the total pressure recovery coefficient,on the other hand,the radial leading edge went against the vent of the flow near the inlet,which result in more flow with low total pressure near the throat and exit of inlet,and the loss of total pressure of the inlet would be larger,therefore,the influence of the radial leading edge to the performance of inlet should make a comprehensive evaluation.
作者
焦子涵
王雪英
邓帆
陈林
王剑颖
黄天
Jiao Zihan Wang Xueying Deng Fan Chen Lin Wang Jianying Huang Tian(Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China Department of Mechanical Engineering, University of Sheffield, Sheffield S1 3JD, United Kingdom)
出处
《战术导弹技术》
北大核心
2017年第1期40-46,共7页
Tactical Missile Technology
