Aerodynamic performance investigation on waverider with variable blunt radius in hypersonic flows

Li, Shibin; Wang, Zhenguo; Huang, Wei; Xu, Shugen; Yan, Li

doi:10.1016/j.actaastro.2017.05.001

Cited by 24 publications

(5 citation statements)

References 33 publications

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“…According to Heiser and Pratt [53], specific impulse of ramjets/scramjets could be estimated by (33) where, η KE is kinetic efficiency; h t0 is the specific total enthalpy, as shown in (34).…”

Section: Subsystem 3: Propulsionmentioning

confidence: 99%

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Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

et al. 2019

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In the design of hypersonic cruise vehicles, great effort is demanded to improve the performances of subsystems, namely structure, aerodynamics, and propulsion. Herein, effort demanded to realize a subsystem performance is quantified by technical merit. To achieve a feasible design, excessive technical merit of any one subsystem should be avoided. Accordingly, a lowest-technical-merit (LTM) design methodology has been proposed in this work. By this methodology, the design problem could be interpreted into a parametric optimization. The solution to such an optimization corresponds to the highest feasibility. The methodology has been implemented on two cases: deriving a hydrocarbon-fueled long-range cruiser from Boeing X-51A, and a hydrogen-fueled LAPCAT scenario from PREPHA. The simulation results show that LTM could achieve optimal allocations while satisfying different payload/range performances. The design methodology could help to improve the feasibility of hypersonic cruise vehicles. Furthermore, it could also be used in the design of other systems.

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Section: Subsystem 3: Propulsionmentioning

confidence: 99%

“…The heat flux at the leading edge is in negative correlation with the local radius of curvature. That means a trade-off of bluntness is demanded [33]. Hence thermal protection would put forward a restriction for aerodynamic performance.…”

mentioning

confidence: 99%

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

et al. 2019

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“…On similar lines, experiments as well as numerical simulations were carried out by Liu et al [33] on a blunt waverider under different angles of attack. Novel blunting methods [34,35] have also been aimed to improve aerodynamic performance alongside reducing aerothermal loads.…”

Section: Introductionmentioning

confidence: 99%

Development of maximum conical shock angle limit for osculating cone waveriders

Ghosh,

Rao

2024

Aerospace Science and Technology

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“…It shows that the heat-transfer rate at the stagnation point varies inversely with the square root of the head blunt radius, while the lift-to-drag ratio inversely with the head blunt radius [35,36]. To accommodate the variation of thermal load at different positions and to reduce aerodynamic losses, a method with the nonuniform blunt radius is proposed and studied [37].…”

Section: Introductionmentioning

confidence: 99%

A Novel Method for Blunting the Leading Edge of Waverider with Specified Curvature

Liu

Ding

et al. 2020

International Journal of Aerospace Engineering

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An ideal waverider has an infinite sharp leading edge, which causes difficulty for manufacture and aerothermal protection. Therefore, the leading edge of the waverider must be blunted. For this purpose, a parametric method for blunting the leading edge of the waverider is proposed here, which can fulfill the goals of setting a leading-edge blunt radius, achieving geometric continuity, and realizing the parametric design. First is the blunting procedure of the proposed method incorporating the construction of two-dimensional blunt curves and the integration of these curves on a three-dimensional waverider configuration. Second, waveriders blunted with different geometric continuities are built with corresponding computing grids generated. Numerical methods are then introduced and validated by the benchmark cases. Finally, results from these blunted configurations are presented and compared in terms of their geometric and flow characteristics. It shows that the proposed method has a better performance in the head region of the waverider and is thereby more suitable for the practical design.

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Aerodynamic performance investigation on waverider with variable blunt radius in hypersonic flows

Cited by 24 publications

References 33 publications

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Development of maximum conical shock angle limit for osculating cone waveriders

A Novel Method for Blunting the Leading Edge of Waverider with Specified Curvature

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