摘要
研究固体冲压发动机进气道优化问题，为降低弹用超声速进气道的外部阻力和提高导弹飞行速度，提出了一种具有低外阻特性的反折式二元进气道方案，明确设计流程和主要设计参数的选取，并针对2～3．5Na速度范围的应用需求开展了方案设计。进一步采用Fluent软件进行数值仿真，研究了反折式进气道的流场特性和性能水平，并与传统设计方案进行了对比。结果表明，在捕获流量相同的条件下，反折式进气道比原方案具有更小的外部阻力及外廓尺寸，还能保持与原方案相当的总压恢复性能，满足工程应用需求，为设计提供依据。
A low drag, reflective, supersonic 2 -D inlet is proposed to reduce external drag of missile inlet and increase missile flight speed. And essential design process and major parameter selection are also ascertained. Ai- ming at the application requirements for the range of 2 to 3.5 Mach, the scheme is worked out carried out. Through numerical simulation with FLUENT, flow characteristicg and performance of reflective inlet are analyzed and com- pared with designs in literatures. Results show that under the same captured flow condition, reflective inlet has lower external drag and dimension, while keeping comparable total pressure recovery performance with conventional design, and is suitable for engineering applications.
出处
《计算机仿真》
CSCD
北大核心
2010年第4期67-70,共4页
Computer Simulation
基金
总装创新项目(7130918)
