Waverider Configurations Derived from Inclined Circular and Elliptic Cones

Rasmussen, Maurice L.

doi:10.2514/3.57771

Cited by 130 publications

(37 citation statements)

References 10 publications

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“…Here we present the results of a set of simulations conducted at a Mach number of 8 and Reynolds number of 8.316x10 6 based on the length of the forebody geometry. We are seeking to maximize two objectives: the lift to drag ratio (L/D) and the volumetric efficiency (V/A, volume of the forebody geometry/wetted area excluding the base plane).…”

Section: Parameterization Flexibility Studiesmentioning

confidence: 99%

“…Since the introduction of the idea, various approaches to designing such geometries have been proposed [4][5][6], the majority of which are inverse design methods where the bodies are generated utilizing calculated supersonic flowfields and stream tracing techniques. Early inverse design methods were based on planar and axisymmetric shockwave flowfields, both of which were limited by the poor balance of L/D ratios, volumetric efficiency and ease of engine inlet integration.…”

Section: Introductionmentioning

confidence: 99%

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Efficient Parameterization of Waverider Geometries

Kontogiannis

Sóbester

Taylor

2017

Journal of Aircraft

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This paper summarizes the results of investigations into the development of parametric waverider geometry models, with emphasis on their efficiency, in terms of their ability to cover a large feasible design space with a sufficiently small number of design variables to avoid the 'curse of dimensionality'. The work presented here is focused on the parameterization of idealized waverider forebody geometries that provide the baseline shapes upon which more sophisticated and realistic hypersonic aircraft geometries can be built. We consider three different aspects of rationalizing the decisions behind the parametric geometry models developed utilizing the osculating cones method. Initially, we discuss three different approaches to the design method itself. Each approach provides direct control over different aspects of the geometry for which very specific shapes would be more complex to obtain indirectly, thus enabling the geometry to more efficiently meet any related design constraints. We then look into a number of requirements and limitations that affect the available options for the parametric design-driving curves of the inverse design method. Finally, we estimate the performance advantages that open up with increasing flexibility of the design-driving curves in the context of a design optimization study. This allows us to reduce the risk of over-parameterizing the geometry model, while still enabling a variety of meaningful shapes. While we mainly used the osculating cones method here, most of the findings also apply to other similar inverse design algorithms. Nomenclature

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Section: Parameterization Flexibility Studiesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Efficient Parameterization of Waverider Geometries

Kontogiannis

Sóbester

Taylor

2017

Journal of Aircraft

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“…It is worth noting that the osculating cones method itself was developed with inlet design in mind. At this stage we have been mostly using the osculating cones method for both, though the osculating axisymmetry 3 and osculating flowfield 4 extensions of the method can potentially further improve the configuration. After describing the geometry generation process, we will look into how it can be integrated onto waverider forebodies generated with inverse design methods.…”

Section: Introductionmentioning

confidence: 99%

“…Waveriders are lifting body geometries designed to keep the shockwave generated by the oncoming hypersonic flow attached to the entire leading edge, effectively trapping the high-pressure region behind the shockwave at the underside of the body, greatly increasing the lift. Since their introduction, inverse design methods have been extensively used to generate such geometries [1][2][3][4] , usually based on planar or axisymmetric flowfields. One of the later and more flexible inverse design methods for generating waverider and inlet geometries is the osculating cones method 5 , which has also been further developed to allow greater flexibility in defining the shock generating body on each osculating plane [6][7] .…”

Section: Introductionmentioning

confidence: 99%

Parametric Geometry Models for Hypersonic Aircraft: Integrated External Inlet Compression

Kontogiannis

Taylor

Sóbester

2016

54th AIAA Aerospace Sciences Meeting

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In this paper we are investigating a method for the design and integration of 3D external compression inlet geometries on parametric geometries of air-breathing hypersonic aircraft. We view the geometries as the first stage of a mixed compression inlet. The investigations are based on waverider geometries generated with the osculating cones waverider forebody design method. The osculating cones method is further utilized to create a second compression surface before the inlet cowl, essentially creating a second waverider geometry on the underside of the forebody. This way, we achieve greater compression for the part of the flow to be captured by the inlet cowl using a geometry that does not require sidewalls (like 2D ramps do), and has a potentially larger capture area than axisymmetric inlet geometries such as half-cones. The integration method is explained in detail, validated and further examined with CFD simulations.

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“…It adds higher stealth characteristics to the inlet [2] and helps in reduction of aircraft weight by replacing its inlet mechanism [3,4,5].Also, Diverter less Supersonic Inlet (DSI) provides favorable mass flow rates as compared to clean intake [6].The parent theory behind the design of bump is based on Waverider concept [7].…”

Section: Introductionmentioning

confidence: 99%