Research on Control Laws and Wall Attachment Characteristics of Four-Way Axisymmetric Aerodynamic Vectoring Nozzles Under Low-Speed Jet Conditions

Fluidic thrust vectoring technology has emerged as one of the key research hotspots in next-generation advanced aircraft design, owing to its compact structure, rapid response and low weight penalty. The aerodynamic vectoring nozzle serves as the core component of this technology. Currently, research on four-way axisymmetric fluidic thrust vectoring nozzles remains limited, and corresponding experimental studies suffer from high costs and strict technical requirements. To fill this gap, this paper presents an experimental study on the control laws of an aerodynamic vectoring nozzle prototype under low-speed jet conditions for preliminary design verification. Taking this nozzle type as the research object, the jet deflection characteristics under various wall configurations are investigated at a jet exit velocity of approximately 80 m/s. Among the four evaluated Coanda wall structures, the composite design integrating a smooth curved front section and a beveled rear–middle section is finally determined. Its key performance indicators meet the engineering requirements: a maximum deflection angle of 13.6°, a control linearity of 87.1% for pitch (vertical) control and 89.8% for yaw (lateral) control, a thrust loss of 4%, and a response rate of no less than 200°/s. This work provides a valuable reference for subsequent practical engineering applications.