Aerodynamic configuration integration design of hypersonic cruise aircraft with inward-turning inlets

Wang, Jifei; Cai, Jinsheng; Liu, Chuanzhen; Duan, Yanhui; Yu, Yaojie

doi:10.1016/j.cja.2017.05.002

Cited by 14 publications

(2 citation statements)

References 23 publications

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“…With supercomputer emerging and developing, large-scale numerical simulation becomes feasible, nevertheless, computation resource is finite and expense is difficult to bear, so other method is in demand to explore to improve computation efficiency. Wang et al [15] propose a novel airframe/propulsion integration design method of high speed cruise aircraft, in order to evaluate the performance, the CFD method is used to perform numerical calculation on the design point, the results show a high level of compression efficiency and flow uniformity for the inlet, which enhances the design efficiency of high speed vehicle. Jiao et al [16] perform an unsteady viscous numerical simulation to study the starting process of a high speed nozzle coupled with a simplified inlet model, the impact of the initial backpressure on the pulse-starting characteristics of high speed nozzle-inlet is studied.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation and Efficiency Analysis of Engine-Airframe Integration High speed Vehicle based on Fragment Computation

Chen,

Liu,

Zhang

et al. 2024

Preprint

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The performance analysis of the internal/external flows around a high speed vehicle in near-space is fundamental and critical to the configuration and structure design for high speed aircraft. In this paper, the two-dimensional coupled implicit Reynolds Average Navier-Stokes (RANS) solver and RNG k–ε turbulence model is employed to numerically simulate the flow field of an integrated high speed vehicle. The flow field are divided three parts to solve separately and compared with that solved by integrated simulation. The flow field are decomposed to save computer storage and simulation time. The first part is inlet/isolator, the second part is combustion chamber and the third is nozzle. In the computation process, the outlet condition of isolator is endowed to the inlet boundary of combustion chamber and the outlet boundary of combustion chamber is endowed to the inlet boundary of nozzle, then the whole flow field of integrated high speed vehicle is solved. Aerodynamic characteristic of fragment-computation and integration-computation is comparatively analyzed at different angles of attack, the results show that the maximum deviation of lift coefficient obtained by fragment-computation is less than 3% compared with that by integration, the maximum deviation of drag coefficient fragment-computation is less than 5% compared with that by integration, while pitching moment coefficient deviation less than 12%. However, for simulation time-consumption, the time used by fragment-computation reduces 45% compared with integration-computation. Meanwhile, by components force analysis, it can be concluded that the aerodynamic property of inlet/isolator can been obtained separately and hardly effected by other parts.

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Section: Introductionmentioning

confidence: 99%

Numerical Investigation and Efficiency Analysis of Engine-Airframe Integration High speed Vehicle based on Fragment Computation

Chen,

Liu,

Zhang

et al. 2024

Preprint

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“…Various common 2D and 3D shapes can be parametrically expressed using this method. Many scholars have recently used this method to implement parametric representations of geometry [17][18][19] and have developed several improvements [20][21][22]. Notably, the existing 3D CST methods are described in Cartesian coordinates and cannot directly parametrically represent the 3D asymmetric expansion nozzle with the control line distributed along the circumferential direction.…”

Section: Introductionmentioning

confidence: 99%

Optimal Design of Three-Dimensional Circular-to-Rectangular Transition Nozzle Based on Data Dimensionality Reduction

Yang

et al. 2022

Energies

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The parametric representation and aerodynamic shape optimization of a three-dimensional circular-to-rectangular transition nozzle designed and built using control lines distributed along the circumferential direction were investigated in this study. A surrogate model based on class/shape transformation, principal component analysis and radial basis neural network was proposed with fewer design parameters for parametric representation and performance parameter prediction of the three-dimensional circular-to-rectangular transition nozzle. The surrogate model was combined with Non-dominated Sorting Genetic Algorithm-II to optimize the aerodynamic shape of the nozzle. The results showed that the surrogate model effectively achieved the parametric representation and aerodynamic shape optimization of the three-dimensional circular-to-rectangular transition nozzle. The geometric dimensions and performance parameters of the parametric reconstructed model were comparable to that of the initial model, implying that they can meet the needs of optimal design. The axial thrust coefficient and lift of the optimized nozzle were increased by approximately 0.742% and 15.707%, respectively.

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3D inverse method of characteristics for hypersonic bump-inlet integration

2020

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Aerodynamic configuration integration design of hypersonic cruise aircraft with inward-turning inlets

Cited by 14 publications

References 23 publications

Numerical Investigation and Efficiency Analysis of Engine-Airframe Integration High speed Vehicle based on Fragment Computation

Numerical Investigation and Efficiency Analysis of Engine-Airframe Integration High speed Vehicle based on Fragment Computation

Optimal Design of Three-Dimensional Circular-to-Rectangular Transition Nozzle Based on Data Dimensionality Reduction

3D inverse method of characteristics for hypersonic bump-inlet integration

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