基于多缝放气自适应流动控制的超声速进气道数值研究  

Numerical investigation on adaptive flow-control of supersonic inlet based on air-bleeding multi-slots

作　　者：温玉芬[1] 张晨凯 张正 高晶晶[1] WEN Yufen;ZHANG Chenkai;ZHANG Zheng;GAO Jingjing(China Academy of Launch Vehicle Technology,China Aerospace Science and Technology Corporation,Beijing 100076,China;China Academy of Aerospace Aerodynamics,China Aerospace Science and Technology Corporation,Beijing 100074,China)

机构地区：[1]中国航天科技集团公司中国运载火箭技术研究院,北京100076 [2]中国航天科技集团公司中国航天空气动力技术研究院,北京100074

出　　处：《航空动力学报》2021年第10期2017-2028,共12页Journal of Aerospace Power

摘　　要：针对一种超声速混压式二元进气道,设计了多缝放气自适应流动控制方案,采用数值方法分别对有放气措施和无放气措施的进气道特性进行仿真对比分析,获得了放气对进气道自起动能力、临界性能及阻力特性的影响规律。结果表明:在进气道内收缩段开设系列放气缝,可以在保证进气道自起动能力的情况下大幅提升其临界性能,同时该种流动控制措施可通过唇口斜激波及其反射激波的移动实现放气量的自适应调节。对比分析发现,所设计的多缝放气流动控制方案,在设计状态下进气道的抗反压能力和总压恢复系数较无放气措施方案分别提高12.15%和7.11%,流量损失和阻力增加仅为0.71%和2.7%;巡航状态下,阻力增幅进一步减小,仅为1%。An adaptive flow-control method based on air-bleeding multi-slots for a supersonic mixed-compression two-dimensional inlet was brought forward.Two inlet models with/without air-bleeding method were designed separately and a comparison of the inlet performance was conducted with numerical method.Effects of air-bleeding on the self-starting ability,critical performance and resistance characteristic were attained.Results indicated that setting a series of airbleeding slots in the internal contraction region of the inlet can obviously improve the critical performance of the inlet without deterioration to its self-starting characteristics.Meanwhile,bleeding mass flow can be self-regulated with the movement of the incident shock of the lip and its reflected shock.Compared with the inlet without flow-control method,the maximum backpressure and the total pressure recovery coefficient of the inlet was raised by 12.15% and 7.11% separately at design operation by means of air-bleeding,with a cost of only 0.71% reduction of mass flow and 2.7% resistance increment.Moreover,the increment of resistance can be further reduced to only 1% at cruise operation.

关 键 词：超声速进气道 流动控制 放气 总压恢复系数 阻力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]