Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

Saadia Afridi, Tariq Amin Khan (), Syed Irtiza Ali Shah, Taimur Ali Shams, Kashif Mehmood, Wei Li and David Kukulka ()
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Saadia Afridi: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Risalpur 24090, Pakistan
Tariq Amin Khan: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Risalpur 24090, Pakistan
Syed Irtiza Ali Shah: Department of Mechanical and Aerospace Engineering, Air University, Islamabad 44000, Pakistan
Taimur Ali Shams: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Risalpur 24090, Pakistan
Kashif Mehmood: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of Sciences and Technology, Risalpur 24090, Pakistan
Wei Li: Department of Energy Engineering, Zhejiang University, 38 Zheda Road, Hangzhou 310027, China
David Kukulka: Department of Mechanical Engineering, State University of New York College at Buffalo, 1300 Elmwood Avenue, Buffalo, NY 14222, USA

Energies, 2023, vol. 16, issue 2, 1-20

Abstract: Modern aircraft and missiles are gradually integrating thrust vector control systems to enhance their military capabilities. Bypass Dual-Throat Nozzle (BDTN) control is a new fluidic thrust vectoring technique capable of achieving superior performance with large vector angles and low thrust loss. In this study, we analyzed the flow characteristics and performance parameters of BDTN by varying the bypass angle, nozzle convergence angle, and bypass width. The flow governing equations are solved according to a finite volume discretization technique of the compressible RANS equations coupled with the Renormalization Group (RNG) k-ϵ turbulence model for Nozzle Pressure Ratio (NPR = 2~10) to capture the significance of under-expanded and over-expanded jets. Results show that by decreasing the bypass angle from 90° to 35°, there is a 6% increase in vectoring angle while the vectoring efficiency is enhanced by 18%. However, a decrease of 3% in the thrust and discharge coefficients is also observed. When the convergence angle was increased from 22° to 37°, vectoring angle, discharge coefficient, and thrust coefficient increased by 2%, 1%, and 0.26%, respectively. Moreover, vectoring efficiency is also enhanced by 8% by reducing the convergence angle from 37° to 22°. Based on the investigated parameters, it is determined that nozzle convergence angle does not significantly influence thrust vectoring performance, however, bypass width and bypass angle have a significant effect on thrust vectoring performance.

Keywords: bypass dual throat nozzle; thrust vectoring; vectoring performance; nozzle configurations (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2023
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