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.
作者
温玉芬
张晨凯
张正
高晶晶
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)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2021年第10期2017-2028,共12页
Journal of Aerospace Power
关键词
超声速进气道
流动控制
放气
总压恢复系数
阻力
supersonic inlet
flow-control
air-bleeding
total pressure recovery coefficient
resistance
