摘要
利用基于乘波理论的Bum p进气道设计软件,据锥型流精确流线法设计了一腹部进气布局的Bum p进气道。用CFD模拟手段,从对称面马赫数分布、凸包上的极限流线及横截面上压强系数分布等方面分析了进气道进口段流场特征,证明所设计的Bum p进气道流动特征符合预期设计目标。通过CFD计算和试验对比,分析了所设计的Bum p进气道超声速气动性能,表明在发动机设计状态,在来流马赫数M a∞为2.0时,出口平均总压恢复系数接近0.87,而在M a∞=1.8时该值不低于0.91。
Using an engineering design software of bump inlet based on waverider theory,an under fuselage bump inlet was designed based on the conic flow accurate stream line method. With regard to distribution of Math numbers in the symmetric plane,limiting stream lines on the bump surface and distribution of pressure recovery coefficient （Cp） in the cross-section,the flow characteristics of the inlet were analyzed. It is shown that flow characteristics of the designed bump inlet are well consistent with the theoretical analysis with ideal gas. Supersonic aerodynamic properties of the bump inlet were analyzed by comparing the experimental results with computational ones. The results show that under design point condition,the average total pressure recovery coefficient at exit of bump inlet is nearly 0. 87 at design Mach number of 2. 0,and no less than 0. 91 at mach number of 1.8.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第5期740-745,共6页
Journal of Aerospace Power
基金
航空科学基金资助(00C52035)
关键词
航空、航天推进系统
凸包进气道
无隔道超声速进气道
进气道设计
流场
总压恢复系数
aerospace propulsion system
bump inlet
Diverterless Supersonic Inlet （DSI）
inlet design
flow field
total pressure recovery coefficient
