An overview of research on waverider design methodology

Ding, Feng; Liu, Jun; Shen, Chibing; Liu, Zhen; Chen, Shao-hua; Fu, Xilin

doi:10.1016/j.actaastro.2017.08.027

Cited by 60 publications

(15 citation statements)

References 45 publications

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“…When the angle of the slope at the point 3 is zero degrees, and the coordinate values (z, y) at point 2 and point 3 are given in Eq. (14), the curve 2-3 and 7-17 can be determined.…”

Section: (7)mentioning

confidence: 99%

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An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

et al. 2019

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With the aims of overcoming the limitations of the existing basic flow model derived from an axisymmetric generating body and extending the aerodynamic design method of the airframe/inlet integrated waverider vehicle, this study develops an upgraded basic flow model derived from an axisymmetric shock wave. It then upgrades the design method for airframe/inlet integration of an air-breathing hypersonic waverider vehicle, which is termed the ‘full-waverider vehicle’ in this study. In this paper, first, the design principle and method for the upgraded full-waverider vehicle derived from an axisymmetric basic shock wave are described in detail. Second, an upgraded basic flow model that accounts for both internal and external flows is derived from an axisymmetric basic shock wave by use of both the streamline tracing method and the method of characteristics (MOC). Third, the upgraded full-waverider vehicle is developed from the upgraded basic flow model by the streamline tracing method. Fourth, the design theories and methodologies of both the upgraded basic flow model and the upgraded full-waverider vehicle are validated by a numerical computation method. Finally, the aerodynamic performances and viscous effects of both the upgraded basic flow model and the upgraded full-waverider vehicle are analysed by numerical computation. The obtained results show that the upgraded basic flow model and aerodynamic design method are effective for the design of the airframe/inlet integration of an air-breathing hypersonic waverider vehicle.

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“…When the angle of the slope at the point 3 is zero degrees, and the coordinate values (z, y) at point 2 and point 3 are given in Eq. (14), the curve 2-3 and 7-17 can be determined.…”

Section: (7)mentioning

confidence: 99%

“…The waverider first proposed by Nonweiler (7) in 1959 is any hypersonic lifting body with an attached shock wave along its leading edge (8)(9)(10)(11)(12)(13)(14) . Since then, because of the excellent aerodynamic configuration of the waverider, it has become one of the most ideal aerodynamic configurations for hypersonic vehicles.…”

Section: Introductionmentioning

confidence: 99%

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

et al. 2019

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“…With (23) substituted into (19), W E could be contained in the function term aW . Then the gross weight could be revised as W = aW + bW P + W F (24) With two sides of (24) divided by gross weight, the payload capacity of the HCV could be estimated by…”

Section: Design Problem Of a Hypersonic Cruise Vehicle A Systemmentioning

confidence: 99%

“…This is the reason for the decline of theoretical aerodynamic performance. To improve the aerodynamic performance, waverider [23], [24], counterflowing aerospike/aerodisk [25]- [27], high-slenderness configurations [27], [28] have been proven effective. However, the aerodynamic performance of waverider is difficult to maintain when engine and control panels are integrated [29], [30].…”

mentioning

confidence: 99%

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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“…Huang Wei et al 13 studied the influence of different parameters (inflow Mach number, angle of attack and sideslip angle) on the aerodynamic performance of hypersonic waverider vehicle. Ding Feng published several papers 8,[14][15][16][17][18] on the design method and fullscale waverider design, which provides an important reference for the design and application of waverider. Cui Kai et al [19][20][21] used a new method to derived the waverider configuration from the general conical flow field.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on aerodynamic performance of waverider with a new bluntness method

Xiao

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Abastrct The waverider is deemed the most promising configuration for hypersonic vehicle with its high lift-to-drag ratio at design conditions. However, considering the serious aero-heating protection, the sharp leading edge must be blunted. The existing traditional bluntness methods including the following two types: “reducing material method” and “adding material method”. Compared to the initial waverider, the volume will be smaller or larger using the traditional methods. With the fixed blunted radius, the volume and aerodynamic performance is determined. In this paper, a new bluntness method which is named “mixing material method” is developed. In this new method, a new parameter is introduced based on the traditional two bluntness methods. Under fixed blunted radius, the volume and aerodynamic performance can be changed within a wide range by adjusting the parameter. When the parameter is 0 and 1, the novel blunted method degenerated into the “reducing material method” and “adding material method” respectively. The influence of new parameter on the aerodynamic characteristics and volume are studied by numerical simulation. Results show that the volume, lift and lift-to-drag ratio increases with the increase of the parameter under the fixed blunt radius, but simultaneously, the drag will also increase. Therefore, considering the different requirements of the air-breathing hypersonic aircrafts for the balance of thrust and drag, lift and weight, a suitable bluntness parameter can be selected to achieve a balance. This research can provide reference for hypersonic waverider vehicle design.

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An overview of research on waverider design methodology

Cited by 60 publications

References 45 publications

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Numerical study on aerodynamic performance of waverider with a new bluntness method

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