As a critical component of an aircraft engine, the nozzle’s primary function is to expand and accelerate the high-temperature, high-pressure exhaust gases from the turbine and expel them from the airframe, thereby generating engine thrust. By adjusting the nozzle throat area, the distribution of gas expansion ratios between the turbine and the nozzle can be altered, changing the operating point of the compressor and turbine to control the engine’s working state. This adjustment modifies the engine’s thrust and fuel consumption rate, improves startup performance, and minimizes the impact on engine operation when engaging or disengaging afterburners (Lian 2005). With advancements in aviation technology and evolving air combat requirements, the functions of nozzles have expanded. For example, they now provide thrust vectoring, supplementing or replacing aerodynamic control surfaces during low-speed and high-angle-of-attack flight to enable post-stall maneuvers. This reduces the weight, drag, and radar cross-section of aerodynamic surfaces while shortening takeoff and landing distances. Additionally, nozzles can control infrared radiation signatures, radar cross-sections, and noise levels, enhancing the aircraft’s infrared stealth, radar stealth, and acoustic stealth capabilities, thereby improving survivability (Gao et al. 1995). Therefore, the fundamental requirements for aircraft engine nozzles are: minimal internal losses and external drag; low infrared radiation levels and small effective scattering surfaces; thrust vector control during takeoff, landing, and combat maneuvers (for agile aircraft); and low noise levels (within permissible limits) (Cui and Xu 2018; Liu 2002).