Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle

Compared to a variety of mechanical vectoring nozzles, fluidic vectoring nozzles possess more research value nowadays. The dual throat nozzle is gradually developing into an outstanding technology to handle supersonic and hypersonic aircraft deflections. Three-dimensional, steady, compressible, and...

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Bibliographic Details
Published in:Journal of Applied Fluid Mechanics 2021-01, Vol.14 (1), p.73-87
Main Authors: Wu, K X, Kim, T H, Kim, H D
Format: Article
Language:English
Subjects:
Aerodynamics
Compressibility
Computational fluid dynamics
Computer applications
Efficiency
Fluid dynamics
Fluid flow
Hydrodynamics
Hypersonic aircraft
Injection
Injectors
K-omega turbulence model
Momentum
Nozzles
Pressure ratio
Reynolds averaged Navier-Stokes method
Shear stress
Supersonic aircraft
Throats
Thrust vector control
Turbulence models
vector control
jet deflection
shock wave
compressible flow
internal flow
Viscous flow
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Summary:Compared to a variety of mechanical vectoring nozzles, fluidic vectoring nozzles possess more research value nowadays. The dual throat nozzle is gradually developing into an outstanding technology to handle supersonic and hypersonic aircraft deflections. Three-dimensional, steady, compressible, and viscous flows in rectangular dual throat nozzles are numerically investigated by resolving Reynolds-averaged Navier-Stokes equations and shear stress transport k-omega turbulence model. Computational fluid dynamics results are verified against the existing experimental data, where a good consistency is gained. The impacts of nozzle pressure ratio, injection-to-mainstream momentum flux ratio, and setup angle of the slot injector on the systemic performance are examined. Useful conclusions are summarized for engineering designers. Firstly, pitching angles decline along with an increasing nozzle pressure ratio, while systemic thrust ratio and thrust efficiency increase. Secondly, thrust vector angles enlarge with an increase of the injection-to-mainstream momentum flux ratio, whereas both systemic thrust ratio and thrust efficiency decay. Finally, the setup angle of the slot injector impacts the systemic performance remarkably. Although the pitching angle for the setup angle of 120° is highest, comprehensive characteristics in terms of systemic thrust efficiency and systemic thrust ratio for the setup angle of 150° are more excellent.
ISSN:1735-3572
1735-3645
DOI:10.47176/jafm.14.01.31690