An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles

Ding, Feng; Liu, Jun; Shen, Chibing; Huang, Wei; Liu, Zhen; Chen, Shao-hua

doi:10.1016/j.actaastro.2018.09.002

Cited by 61 publications

(15 citation statements)

References 45 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…region D-M-N-R as shown in Fig. 3), from the inlet lip curve (curve 2-1-7) and the leading-edge curves of two wings (curves 3-2 and 7-17) downstream, up to the base plane; this also simultaneously yields the trailing-edge curve of the fuselage belly (curve 14-15-16) and the trailing-edge curves of two wings (curves 3-14 and [16][17].…”

Section: The Basic Flow Field Of This Model Is Divided Into Two Regiomentioning

confidence: 86%

“…In this case, the leading-edge curves of the forebody and two wings are expressed by the projection curves of the leading-edge curves on the base plane, and both the leading-edge curves and the corresponding projection curves are marked with the same notations for convenience. The output curves obtained by tracing the streamlines in the basic flow model include the inlet exit curve (curve 10-12-11-13), the trailing-edge curve of fuselage belly (curve 14-15-16) and the trailing-edge curves of two wings (curve 3-14, [16][17].…”

Section: (7)mentioning

confidence: 99%

See 1 more Smart Citation

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

et al. 2019

View full text Add to dashboard Cite

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.

show abstract

Section: The Basic Flow Field Of This Model Is Divided Into Two Regiomentioning

confidence: 86%

Section: (7)mentioning

confidence: 99%

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

et al. 2019

View full text Add to dashboard Cite

show abstract

“…The components of system-gross technical merit are shown in Table. 6 The growth coefficients of the subsystems are set as 0.5. The weight factors are estimated by the strategy in (15) and the levels in Table. 5. Table. 6 indicates that propulsion possesses the lowest weight factor, followed by aerodynamics.…”

Section: Ltm Design Of Hypersonic Cruise Vehicles a Interpretatimentioning

confidence: 99%

“…Because of these problems, propulsive performance of HCV is difficult to realize and improve [14]. To solve these problems, techniques such as waverider forebodies [15], novel configurations of inlets/diffusers (for example, Busemann inlet [16] and Lens Analogy inlet/diffuser [17], [18]), precooling [19], recycling of energy [20], and active control (for example, control system with a combination of Wheeler Doublets and vortex generator jets [21]) have become research focuses. However, adoption of these techniques would also introduce new problems, for example, higher empty weight caused by additional components.…”

mentioning

confidence: 99%

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

et al. 2019

View full text Add to dashboard Cite

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.

show abstract

“…There is a clear hysteresis loop during the shock train oscillation. Ding et al [19] worked on the design of a waverider concept that can be used in an air-breathing hypersonic vehicle. They concluded that the basic flow field for the design of the air-breathing hypersonic wave rider vehicles is no longer confined to a conical flow field with a straight shock wave but is instead further extended to an axisymmetric flow field with a curved shock wave.…”

Section: Introductionmentioning

confidence: 99%

Numerical evaluation of effects of the isolator height and the leading-edge bluntness on a scramjet inlet

Siqueira

Rosa

Ribeiro

2020

J Braz. Soc. Mech. Sci. Eng.

View full text Add to dashboard Cite

Air-breathing hypersonic vehicles can be powered by scramjet (supersonic combustion ramjet) engines, whose inlet requires blunt leading edges in order to overcome the high heat fluxes that are inherent of hypersonic flights. Thus, this work has the purpose of evaluating, through detailed two-dimensional computational fluid dynamics analysis, the influence of the leading-edge bluntness and isolator height on the airflow of a scramjet intake. Three radii have been analyzed for the forebody and cowl leading edges: sharp, 0.5 and 1.0 mm. Moreover, two different isolator heights were varied: 15 and 20 mm. Fixed temperatures of 300 K and 1300 K were considered along the hypersonic vehicle wall. The static temperature, pressure, and Mach number contour are part of the analysis, as well as the Stanton number and the adiabatic kinetic efficiency of the scramjet. It was evidenced that both leading-edge bluntness and isolator height performed great influence on the intake airflow structure. Results showed that the isolator height had a major effect on the flow separation at the isolator entrance yielding a recirculation zone that increases with the isolator height. Furthermore, higher Stanton numbers and temperature along the isolator were found for the shorter isolator height due to stronger shock waves and higher frequency of shock-wave train. The leading-edge bluntness, in this analysis, was taken as a parameter to reduce the heat flux at the stagnation point of leading edges. However, a decrease in the adiabatic kinetic efficiency was observed when the leading-edge radius is increased. Moreover, blunt leading edges promoted a decrease in Stanton number along the scramjet intake walls and also a decrease in average temperatures throughout the isolator.

show abstract

An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles

Cited by 61 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 evaluation of effects of the isolator height and the leading-edge bluntness on a scramjet inlet

Contact Info

Product

Resources

About