Numerical Investigation of Design Parameters for Dual Throat Fluidic Thrust Vectoring Nozzle Using Secondary Injection System

Abstract

Thrust vectoring system is considered one of the most important techniques needed for high-performance supersonic aircraft, which introduces a higher level of capabilities to the aircraft in term of maneuverability. Thrust vectoring is a valuable maneuver effector at low dynamic pressure and post stall high angles of attack by providing controlling abilities in flight regimes where the conventional aerodynamic flight control technologies lose their effectiveness. These regimes include low-speed flight, where dynamic pressure is low, and high angle of attack flight, where flow separation from the wings disturbs the smooth airflow over conventional control surfaces. Thrust vectoring expands the flight envelop beyond the ability of conventional aircraft flight control surfaces. Increase the maneuverability and versatility of aircraft. Superior advantages are achieved with implementing thrust vectoring technology by improving the agility and maneuverability, reducing of aerodynamic controls and cruise trim drag which increase fuel efficiency and shortens the take- off and landing requirements. The concept of thrust vectoring technique depends on deflecting the thrust force of engine exit jet from the centerline to the aimed axis. The two fundamental methods to implement the thrust vectoring within aircraft or missile nozzle are mechanical and fluidic. The mechanical thrust vector method is currently performed using complex arrays of hardware mechanical actuators capable of adapting the nozzle geometry and deflects the jet flow. However, this mechanism increases the weight of the nozzle and required precision