Numerical study of attack angle characteristics for integrated hypersonic vehicle

Huang, Wei; Wang, Zhenguo

doi:10.1007/s10483-009-0612-y

Cited by 33 publications

(11 citation statements)

References 10 publications

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“…The two-dimensional coupled implicit Reynolds Averaged Navier-Stokes (RANS) equations [15] and the RNG k−ε turbulent model are employed to numerically simulate the unheated flow field around the cavities. While no-slip conditions are applied along the wall, and a symmetric condition is imposed on the upper boundary, but due to the flow being supersonic, at the outflow all the physical variables are extrapolated from the internal cells, and the grids are generated by the commercial software Gambit.…”

Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

Drag force investigation of cavities with different geometric configurations in supersonic flow

Luo

Huang

Liu

et al. 2011

Sci. China Technol. Sci.

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In order to prolong the residence time of the flow retaining in the supersonic flow, wall cavity has been widely applied in the scramjet combustor, and this affects the aerodynamic surface and imposes additional drag force on the hypersonic propulsion system. The two-dimensional coupled implicit Reynolds Averaged Navier-Stokes (RANS) equations and the RNG k−ε turbulent model were employed to investigate the flow fields of cavities with different geometric configurations, namely the classical rectangular, triangular and semi-circular, and the cavities with the fixed depth and length-to-depth ratio. At the same time, the drag force performances of the cavities were estimated and compared. The obtained results show that the numerical results are in very good agreement with the experimental data, and the different scales of grid make only a slight difference from the numerical results. The intensity of the trailing shock wave is much stronger than that of the leading one, and the area around the trailing edge of the cavities plays an important role in the chemical reaction in the scramjet combustor. With the fixed depth and length-to-depth ratio, the triangular cavity can strengthen the turbulent combustion in the scramjet combustor further, but impose the most additional drag force on the scramjet engine. The classical rectangular one can impose the least additional drag force on the engine, but the function of strengthening the combustion is the weakest. The influence of the semi-circular one is the moderate, but the machining process is more complex than the other two configurations. aerospace propulsion systems, cavity, drag force, scramjet engine, hypersonic vehicle Citation: Luo S B, Huang W, Liu J, et al. Drag force investigation of cavities with different geometric configurations in supersonic flow.

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Section: Physical Model and Numerical Methodsmentioning

confidence: 99%

Drag force investigation of cavities with different geometric configurations in supersonic flow

Luo

Huang

Liu

et al. 2011

Sci. China Technol. Sci.

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“…The two-dimensional coupled implicit NS equations and standard k-ε turbulent models [18,19] are used to numerically simulate the combustion flow field of the integrated hypersonic vehicle, and the standard wall functions are employed to model the near-wall region flow, non-slip conditions are assumed for the walls of the vehicle, the setting of boundary conditions is shown in Table 2, the effect of cavity flame holder configuration on the combustion flow field performance of the vehicle is investigated. At the outflow, all the physical variables are extrapolated from the internal cells due to supersonic flow.…”

Section: Numerical Methods and Boundary Conditionsmentioning

confidence: 99%

Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle

Huang

Luo

Liu

et al. 2010

Sci. China Technol. Sci.

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As one of the most common methods to be used as the flame holding mechanism in the propulsion system of the integrated hypersonic vehicle, the research of cavity flame holder has drawn an ever increasing attention of many researchers. The two-dimensional coupled implicit NS equations, the standard k-ε turbulent models and the finite-rate/eddy-dissipation reaction model were employed to simulate the experimental items arranged by the orthogonal design, and the variance analysis method was used to investigate the effects of the geometric parameters of the cavity flame holder on the aero-propulsive performance of the integrated hypersonic vehicle, namely the depth, the ratio of length-to-depth and the sweepback angle. The obtained results show that the geometric parameters make only a little difference to the aero-propulsive performance of the vehicle in the range considered in this paper, and the cavity flame holder with its sweepback angle 45° can satisfy the performance requirement of the integrated hypersonic vehicle further. The hydrogen injected from the upper stream of the cavity makes the boundary layer separate on the lower wall of the engine, and a separate region appears in the upper stream and down stream of the injection slot, respectively. aerospace propulsion system, integrated hypersonic vehicle, cavity flame holder, variance analysis, orthogonal design, aero-propulsive performance Citation: Huang W, Luo S B, Liu J, et al. Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle.

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“…One of the key techniques for ensuring the success of air-breathing hypersonic vehicles is the effective integration of the engine with the airframe [1,2]. To reduce overall drag and achieve positive thrust margins at hypersonic speeds, the engine must be incorporated as an integral part of the airframe [3].…”

Section: Introductionmentioning

confidence: 99%

Novel inlet–airframe integration methodology for hypersonic waverider vehicles

et al. 2015

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Numerical study of attack angle characteristics for integrated hypersonic vehicle

Cited by 33 publications

References 10 publications

Drag force investigation of cavities with different geometric configurations in supersonic flow

Drag force investigation of cavities with different geometric configurations in supersonic flow

Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle

Novel inlet–airframe integration methodology for hypersonic waverider vehicles

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