CAJ | 학술논문

采用结构化网格与二阶精度流场分区求解技术,对某冲压发动机超音速进气道特性进行了深入研究.通过数值模拟得到了在飞行高度3000m、飞行速度2.5Ma、不同攻角情况下,超音速进气道内外粘性流场复杂的波系结构,详细分析了攻角对进气道总压、流量等工作参数的影响.结果显示,随着来流攻角的增大,此进气道总压恢复系数变化不大,流量系数逐渐降低,而流场畸变则明显增大.
채용결구화망격여이계정도류장분구구해기술,대모충압발동궤초음속진기도특성진행료심입연구.통과수치모의득도료재비행고도3000m、비행속도2.5Ma、불동공각정황하,초음속진기도내외점성류장복잡적파계결구,상세분석료공각대진기도총압、류량등공작삼수적영향.결과현시,수착래류공각적증대,차진기도총압회복계수변화불대,류량계수축점강저,이류장기변칙명현증대.
By means of block structure grid and second-order zonal solver method,the research on supersonic inlet performance of ramjet was carried out. Complex wave structure of supersonic inlet at 3000m,2.5Ma and different attack angle related to critical status were achieved by numerical simulation. The influence of attack angle on total pressure,mass flow ratio of inlet was analyzed. Results show that the increasing of attack angle,the total pressure recovery changes a little and mass flow ratio reduces.However,flow distortionindex increasers obviously.