Optimization design of energy deposition on single expansion ramp nozzle

Ju, Shengjun; Yan, Chao; Wang, Xiaoyong; Qin, Yupei; Ye, Zhifei

doi:10.1016/j.actaastro.2017.09.004

Cited by 19 publications

(2 citation statements)

References 32 publications

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“…The commercial CFD program ANSYS FLUENT 19.1 is used to simulate the flow field. LES method directly calculates the turbulent motion larger than the grid scale through the unsteady Navier-Stokes (NS) equations, while the influence of small-scale vortices on large-scale vortices is reflected through subgrid model [19,20]. In LES method, two parts are divided for instantaneous variable ϕ, given by…”

Section: Numerical Algorithmmentioning

confidence: 99%

Aerodynamic-Aeroacoustic Optimization of a Baseline Wing and Flap Configuration

Sun

Guo

et al. 2022

Applied Sciences

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Optimization design was widely used in the high-lift device design process, and the aeroacoustic reduction characteristic is an important objective of the optimization. The aerodynamic and aeroacoustic study on the baseline wing and flap configuration was performed numerically. In the current study, the three-dimensional Large Eddy Simulation (LES) equations coupled with dynamic Smagorinsky subgrid model and Ffowcs–William and Hawkings (FW–H) equation are employed to simulate the flow fields and carry out acoustic analogy. The numerical results show reasonable agreement with the experimental data. Further, the particle swarm optimization algorithm coupled with the Kriging surrogate model was employed to determine optimum location of the flap deposition. The Latin hypercube method is used for the generation of initial samples for optimization. In addition, the relationship between the design variables and the objective functions are obtained using the optimization sample points. The optimized maximum overall sound pressure level (OASPL) of far-field noise decreases by 3.99 dB with a loss of lift-drag ratio (L/D) of less than 1%. Meanwhile, the optimized performances are in good and reasonable agreement with the numerical predictions. The findings provide suggestions for the low-noise and high-lift configuration design and application in high-lift devices.

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Section: Numerical Algorithmmentioning

confidence: 99%

Aerodynamic-Aeroacoustic Optimization of a Baseline Wing and Flap Configuration

Sun

Guo

et al. 2022

Applied Sciences

Self Cite

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“…With the support of numerous experiments, the GTX scheme [5] and the ISTAR scheme [6] for RBCC were determined to achieve the thermal throat via combustion and to reach the required thrust and specific impulse using the SERN with a fixed geometric structure. The SERN is the main thrust component of the hypersonic propulsion system, so the design of the nozzle is very important [7]. The design point of the nozzle is slightly smaller than the cruise Mach number [8], which makes the SERN work in a serious overexpansion state at low flight Mach number.…”

Section: Introductionmentioning

confidence: 99%

The Influence of External Flow Field on the Flow Separation of Overexpanded Single-Expansion Ramp Nozzle

Yu,

Mao,

et al. 2023

Aerospace

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Flow separation and transitions of separation patterns are common phenomena of nozzles working with a wide Mach range. The maximum thrust method is applied to design the single-expansion ramp nozzle (SERN) for specific operating conditions. The nozzle is used to numerically simulate the transition processes of separation patterns under the linear change in the external flow Mach number and the actual trajectory take-off condition of a rocket-based combined cycle (RBCC), to investigate the mechanism through which the external flow field influences the separation pattern transition during acceleration. The computational fluid dynamics (CFD) method is briefly introduced, followed by experimental validation. Then, the design procedure of SERN is described in detail. The simulation results indicate that as the external Mach number increases, the flow field in the nozzle undergoes transitions from RSS (ramp) to FSS, and finally exhibits a no-flow separation pattern. The rate at which the external Mach number varies has little effect on the transition principle of the nozzle flow separation patterns, but it has a significant effect on the critical Mach number of the transition points. The external flow field of the nozzle has an airflow accumulation effect during acceleration, which can delay the transition of the flow separation pattern.

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Inverse design method on scramjet nozzles based on maximum thrust theory

Chen

Huang

2020

Acta Astronautica

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Optimization design of energy deposition on single expansion ramp nozzle

Cited by 19 publications

References 32 publications

Aerodynamic-Aeroacoustic Optimization of a Baseline Wing and Flap Configuration

Aerodynamic-Aeroacoustic Optimization of a Baseline Wing and Flap Configuration

The Influence of External Flow Field on the Flow Separation of Overexpanded Single-Expansion Ramp Nozzle

Inverse design method on scramjet nozzles based on maximum thrust theory

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