Experimental Investigation of a Mach 3.5 Waverider Designed Using Computational Fluid Dynamics

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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“…. (12) where r D represents the shock wave radius of the basic flow model at the inlet lip plane, and its value is shown in Eq. (6).…”

Section: (7)mentioning

confidence: 99%

“…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%

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

et al. 2019

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“…Figure 5(b) shows the creation of the bump section after applying the inverse stream-tracing method. These methods are explained in many researches before [13][14][15][16] and, therefore, the details are not explained here. Figure 6(a) shows the final CAD geometry of the DSWD profile.…”

Section: Compression Surfaces For Forebody Designmentioning

confidence: 99%

“…This process is common to other research and concept development in this area. 15,16 Figure 8 simplifies the basic aerodynamic shape design for a DSWD forebody. Table 1 summarizes the computational goals and case studies in this paper.…”

Section: Compression Surfaces For Forebody Designmentioning

confidence: 99%

Design of hypersonic forebody with submerged bump

Saheby

Huang

Hays

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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A double shock waverider forebody configuration, with curved surfaces and known pressure fields and shock arrays, is constructed by a stream-tracing approach. The compression surface consists of a wedge and conical shocks. The conical shock results from a modified wave-derived bump surface that diverts the boundary layer before the inlet entrance. The design is fully computational fluid dynamics based and emphasis is placed on the compact design with boundary layer diverting ability. Controlling or diverting the thick boundary layer safely is a difficult challenge in hypersonic flight vehicle design especially when the inlets are highly integrated with the fuselage. Numerical simulations show that the new combination can divert a significant fraction of boundary layer before the inlet and maintains a good compression ratio for propulsion efficiency at Mach 5.0. Effects of forebody aerodynamics on the integrated inlet and comparisons with other systems are described in this paper.

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“…Because of this advantage, the concept has received a lot of attention over the years after its inception by Nonweiler in 1959 [7]. In the wake of the arrival of a family of viscous optimized waveriders [8], a lot of literature about their design methodologies [9][10][11][12], performance evaluations [13][14][15][16][17][18][19], and proposed applications [20][21][22][23][24][25] was published.…”

Section: Doi: 102514/1j055395mentioning

confidence: 99%

High-Pressure Capturing Wing Configurations

Cui

Xiao

et al. 2017

AIAA Journal

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This paper proposes a family of high-pressure capturing wing configurations that aim to improve the aerodynamic performance of hypersonic vehicles with large volumes. The predominant visual feature of such configurations is a thin wing called a high-pressure capturing wing attached to the top of an upwarp airframe. When flying in the hypersonic regime, high-pressure airflow compressed by the upper surface of the vehicle acts on the high-pressure capturing wing and significantly augments lift on the vehicle with only a small increase in drag, producing a correspondingly high increase in its lift-to-drag ratio. A series of numerical validations were carried out on the basis of both inviscid and viscous computational models in which ideal cones with different cone angles and combined conewaverider bodies with different volumes were used as airframes. The results clearly demonstrate that a configuration using a high-pressure capturing wing has a significantly higher lift (with a correspondingly high value of lift-to-drag ratio) than one without a high-pressure capturing wing, especially for vehicles with large volumes. This paper contains a preliminary, results-based report of the conditions under which high-pressure capturing wing configurations were tested.= cruising speed W = gross weight, width α = angle of attack β = shock-wave angle γ = ratio of specific heats Δn = nondimensional height of the first layer near the wall η = ratio of average pressure on different surfaces θ = wedge angle, half-cone angle ξ = volumetric efficiency ρ = density Subscripts B = body H = high-pressure capturing wing HCWL = lower surface of the high-pressure capturing wing HCWU = upper surface of the high-pressure capturing wing

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Experimental Investigation of a Mach 3.5 Waverider Designed Using Computational Fluid Dynamics

Cited by 34 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

Design of hypersonic forebody with submerged bump

High-Pressure Capturing Wing Configurations

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