摘要
选择进气道外压缩段的气流转折角为设计变量,以进气道的压升比为约束条件,分别以总压恢复系数和阻力系数为优化目标,基于一维气体动力学,在飞行马赫数6,飞行高度25 km,进气道出口气流方向与自由来流夹角等于0,°2,°4°和6°的条件下,对二维混压式高超声速进气道进行了优化设计,得到了优化的斜激波配置。优化结果表明,在所讨论的各种情况下,以阻力系数最小为目标得到的外压缩段斜激波系与以总压恢复系数最大为目标得到的外压缩段斜激波系基本相同,都近似为等强度斜激波系。运用数值模拟手段验证了等强度斜激波系配置原则,本文提供的方法可以用于二维混压式高超声速进气道的初步设计。
Two dimensional mixed compression hypersonic inlets were optimized for maximum total pressure recovery and minimum drag coefficient respectively under the condition of Mach number 6, flight altitude 25 km and the angle between the flow direction at inlet exit and the flow direction of free stream 0° , 2° , 4° and 6°. The external shock turning angles were selected as design variables. The inlet pressure step-up ratio was selected as a constraint. One-dimensional aerodynamics was used in the optimization. The optimum oblique shocks series were attained. Results show that for the same design condition the optimum external oblique shocks series with minimum drag coefficient is almost the same as that with maximum total pressure recovery. Both have oblique shocks series approximately with equal strength. The principial of oblique shocks series with equal strength was validated by method of numerical calculation and it can be used in preliminary design of two-dimensional mixed compression hypersonic inlet.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第2期157-161,共5页
Journal of Propulsion Technology
关键词
高超声速进气道
混压式进气道
斜激波
优化
Hypersonic inlet
Mixed compression inlet
Oblique shock
Optimization
