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Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Author

Listed:
  • Saadia Afridi

    (Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Islamabad 44000, Pakistan)

  • Tariq Amin Khan

    (Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Islamabad 44000, Pakistan)

  • Syed Irtiza Ali Shah

    (Department of Mechanical and Aerospace Engineering, Faculty of Engineering, Air University, Islamabad 44000, Pakistan)

  • Taimur Ali Shams

    (Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Islamabad 44000, Pakistan)

  • Khawar Mohiuddin

    (Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Islamabad 44000, Pakistan)

  • David John Kukulka

    (Department of Mechanical Engineering, State University of New York College at Buffalo, 1300 Elmwood Avenue, Buffalo, NY 14222, USA)

Abstract

Thrust vectoring innovations are demonstrated ideas that improve the projection of aerospace power with enhanced maneuverability, control effectiveness, survivability, performance, and stealth. Thrust vector control systems following a variety of concepts have been considered for modern aircraft and missiles to enhance their military performance. Short Take-off and Landing (STOL) and control effectiveness at lower aircraft speeds can be achieved by employing Fluidic Thrust Vectoring Control (FTVC). This paper summarizes a range of ideas for FTVC that have been designed and tested both computationally and experimentally to determine the thrust vectoring performance of supersonic propulsion system nozzles. The conventional method of thrust vectoring involves mechanical means to deflect the direction of flow of the exhaust gases, whereas the most recent method involves fluidic-based thrust vectoring techniques. Fluid-based thrust vectoring has the advantages of simplicity and low weight over mechanical-based thrust vectoring, which has complex geometry and adds extra weight to the aircraft. The fluidic vectoring control nozzles are divided into seven categories: shock vector, bypass shock vector, counterflow, co-flow, throat skewing, dual throat, and bypass dual throat nozzle control. This paper provides a summary of each fluidic thrust vectoring technique with its characteristics, design, classification, and different operational criteria developed to date and compares the intrinsic characteristics of each technique. Based on the present literature, it is concluded that among all the fluidic control techniques, the bypass dual-throat nozzle control can achieve better thrust vectoring performance with large vector angles and low thrust loss.

Suggested Citation

  • Saadia Afridi & Tariq Amin Khan & Syed Irtiza Ali Shah & Taimur Ali Shams & Khawar Mohiuddin & David John Kukulka, 2023. "Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review," Energies, MDPI, vol. 16(15), pages 1-33, July.
    • Handle: RePEc:gam:jeners:v:16:y:2023:i:15:p:5721-:d:1207495
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    References listed on IDEAS

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    1. Zhang, Qibin & Wang, Ke & Dong, Rongxiao & Fan, Wei & Lu, Wei & Wang, Yongjia, 2019. "Experimental research on propulsive performance of the pulse detonation rocket engine with a fluidic nozzle," Energy, Elsevier, vol. 166(C), pages 1267-1275.
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