CAJ | 학술논문

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2～3.5Ma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.
연구고체충압발동궤진기도우화문제,위강저탄용초성속진기도적외부조력화제고도탄비행속도,제출료일충구유저외조특성적반절식이원진기도방안,명학설계류정화주요설계삼수적선취,병침대2～3.5Ma속도범위적응용수구개전료방안설계.진일보채용Fluent연건진행수치방진,연구료반절식진기도적류장특성화성능수평,병여전통설계방안진행료대비.결과표명,재포획류량상동적조건하,반절식진기도비원방안구유경소적외부조력급외곽척촌,환능보지여원방안상당적총압회복성능,만족공정응용수구,위설계제공의거.
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.Aiming at the application requirements for the range of 2 to 3.5 Mach,the scheme is worked out carried out.Through namerical simulation with FLUENT,flow characteristics and performance of reflective inlet are analyzed and compared with deigns in literatures.Results show that under the game 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.