CAJ | 학술논문

高超声压气机叶栅因适用于战斗机高马赫数飞行、增压比高而成为研究热点，但其损失难以控制，波系结构复杂，激波附面层干扰结果难以预测。基于自开发NUAA程序，对超声压气机平面叶栅流场进行计算分析，并通过与超声压气机平面叶栅试验结果的对比，考察叶栅在不同进口马赫数与气流攻角下的总性能、波系结构与激波位置。结果表明：程序计算的总性能与试验值吻合很好，且能精确捕捉超声叶栅中的激波结构，较好预测叶片表面等熵马赫数分布，可为超声叶栅的设计与结果验证提供支持。
고초성압기궤협책인괄용우전두궤고마혁수비행、증압비고이성위연구열점，단기손실난이공제，파계결구복잡，격파부면층간우결과난이예측。기우자개발NUAA정서，대초성압기궤평면협책류장진행계산분석，병통과여초성압기궤평면협책시험결과적대비，고찰협책재불동진구마혁수여기류공각하적총성능、파계결구여격파위치。결과표명：정서계산적총성능여시험치문합흔호，차능정학포착초성협책중적격파결구，교호예측협편표면등적마혁수분포，가위초성협책적설계여결과험증제공지지。
Supersonic compressor cascade has become a key issue for its high pressure ratio and applying to high speed fighter. But its loss is uncontrolled, the shock wave system is complex and the shock wave and boundary layer interaction are unpredicted. Based on NUAA program for supersonic compressor cascade flowfield, calculation analysis was conducted. And through the comparison between calculation results and experimental investigation, the performance parameters, shock formation and shock location at the condi?tion of different Mach number and attack angle were discussed. The results show that the NUAA program could correctly predict the shock wave structure and surface Mach number distribution, and the simulation results were good agreement with the experimental results. The program is helpful for supersonic compres?sor cascade design and testing result validation.