Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive

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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“…Boundary condition 1-2, 2-3, 3-4, 4-5 Pressure far-field 5-6, 6-7, 7-8, 8-9, 1-10, [10][11][11][12] No-slip 9-12…”

Section: Line Segmentsmentioning

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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“…Wherein, the data of models including CAV, Sänger Spaceplane, X-34, and X-38 are from Ernst's book [7], that of X-33 is from Murphy's work [45], that of Boeing X-51A is from Mutzman's [46], and that of X-43A is from Engelund's [47]. Besides, data in works namely Williams [48], Harloff [49], Feng et al [50], Lewis [30], Wang et al [51], and Huiyu et al [52] are also referred.…”

Section: Subsystem 2: Aerodynamicsmentioning

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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“…For instance, He et al [10] proposed a waverider using the general curved cone as the osculating flow field, named osculating general curved cone (OCC) waverider, the results proved that the OCC waverider had good volumetric characteristics and good flow compression abilities to satisfy the inlet requirements for hypersonic air-breathing vehicles. Ding et al [11], [12] designed a waverider generated from axisymmetric supersonic flow past a pointed von Karman ogive, named ''von Karman waveriders'', he also compared the aerodynamic performance between the new waverider and conventional cone-derived waverider using CFD method, the results showed that the ''von Karman waveriders'' possessed higher lift-to-drag ratio but lower volumetric efficiency than conventional cone-derived waverider. Liu et al [13] investigated a wide-ranged multistage morphing waverider design method based on conical flowfield.…”

Section: Introductionmentioning

confidence: 99%

Waverider Configuration Design With Variable Shock Angle

et al. 2019

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A novel waverider design methodology is proposed with a variable shock angle based on the osculating cones' theory. The expected shape with special requirements can be generated by arranging the distribution of shock angle using the new method. Contrast investigation is conducted on three waveriders, which are designed with constant, decreasing and increasing shock angle distribution starting from symmetry plane at the average shock angle of 12 •. The feasibility of the proposed approach is validated by the computational fluid dynamics (CFD) simulation. The results show that the distribution of shock angle has a significant influence on the lift-to-drag ratio and volumetric efficiency. Waverider with decreasing shock angle owns the greater volume and volumetric efficiency but with weak aerodynamic performance. The waverider with increasing shock angle has a higher lift-to-drag ratio and enhanced the static stability but with lower volumetric efficiency. The performance of waveriders with variable shock angle under off-design and blunted conditions is also investigated, which reveals a great overall aerodynamic performance and good robustness. INDEX TERMS Hypersonic waverider, variable shock angle, lift-to-drag ratio, off-design condition, bluntness.

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Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive

Cited by 47 publications

References 23 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

Waverider Configuration Design With Variable Shock Angle

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