Low speed longitudinal aerodynamic, static stability and performance analysis of a hypersonic waverider

Bykerk, Tamas; Verstraete, Dries; Steelant, Johan

doi:10.1016/j.ast.2019.105531

Cited by 14 publications

(4 citation statements)

References 32 publications

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“…The model is fabricated using an assembly of 3D printed pieces. The model was designed to have removable wings, fins, and horizontal stabilisers to allow future investigations of various control deflection combinations [31,32] as well as flexible structures [33] and, potentially, passive aeroelastic control devices [34,35]. An exploded view of the model is presented in Figure 3.…”

Section: Experimental Investigationmentioning

confidence: 99%

“…To supplement the wind tunnel force measurements and characterise whether the flow features of the SSAM-Gen5 model are consistent with those expected of fifth-generation aircraft, a numerical campaign of Reynolds-Averaged Navier-Stokes (RANS) CFD simulations was also undertaken in the present study. Practices for the solver numerics and spatial resolution were adopted from experience with similar configurations in prior studies by the authors [31,[38][39][40] and are further detailed in subsequent sections.…”

Section: Numerical Investigationmentioning

confidence: 99%

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A Generic Model for Benchmark Aerodynamic Analysis of Fifth-Generation High-Performance Aircraft

Giannelis,

Bykerk,

Vio

2023

Aerospace

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This paper introduces a generic model for the study of aerodynamic behaviour relevant to fifth-generation high-performance aircraft. The model design is presented, outlining simplifications made to retain the key features of modern high-performance vehicles while ensuring a manufacturable geometry. Subsonic wind tunnel tests were performed with force and moment balance measurements used to develop a database of experimental validation data for the platform at a freestream velocity of 20 m/s. Numerical simulations are also presented and validated by the experiments and further employed to ensure the vortex behaviour is consistent with contemporary high-performance platforms. A sensitivity study of the computational predictions from the turbulence modelling approach is also presented. This geometry is the first in a suite of representative aircraft geometries (the Sydney Standard Aerodynamic Models), in which all geometries, computational models, and experimental data are made openly available to the research community (accessible via this link: https://zenodo.org/communities/ssam_gen5/) to serve as validation test cases and promote best practices in aerodynamic modelling.

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Section: Experimental Investigationmentioning

confidence: 99%

Section: Numerical Investigationmentioning

confidence: 99%

A Generic Model for Benchmark Aerodynamic Analysis of Fifth-Generation High-Performance Aircraft

Giannelis,

Bykerk,

Vio

2023

Aerospace

Self Cite

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“…Van Arnhem [12] et al studied the influence of Tail-mounted Propellers on aerodynamic performance and static stability, and considered that the changes in propeller loading due to the airframe-induced flow field are the dominant factor in changing airframe stability and performance. Bykerk [13,14] et al studied the influence factors of hypersonic wave riders' lateral and longitudinal static stability during horizontal take-offs and landings by comparing numerical simulation results and experimental data. Phillips [15] and others studied the contribution of tail dihedral to the static stability of a V-tail by using lift line theory.…”

Section: Introductionmentioning

confidence: 99%

Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt

Pan,

Yue,

Liu

et al. 2023

Aerospace

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In this paper, a morphing aircraft with a deployable flared skirt is proposed, and the influence of the flare skirt on the static stability of hypersonic aircraft is studied. The theoretical model of static stability of slender aircraft is established, and the position of the center of pressure can be used as a theoretical basis to measure static stability. Three-dimensional compressible Reynolds-averaged Navier–Stokes (RANS) solver and an SST k-ω turbulence model are used to analyze the aerodynamic characteristics of the aircraft and the influence effect of the flared skirt on the pressure distribution of the body, and the influence trend on the position of the pressure center is verified. At the same time, the reliability of the code and grid is verified by a classic example, and the results are in good agreement with the experimental data in the current literature. Finally, the static stability of an aircraft with flared skirts with different deployment angles is quantitatively measured by defining the stability derivative at the common point. The results show that the static stability of the aircraft with the same forebody is improved by more than 100% under different flight Mach numbers when the flared skirt deployment angle is 30° compared to 0°.

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“…Numerous design methods have been developed since the 1950s, such as the 2-dimensional approach, 1 the conical waverider, 2 arbitrary 3D flow design, 3 and the osculating-cone method. 4 Recently, several state-of-art design methods are proposed considering the theoretical and engineering requirements, such as low speed performances, 5 variable Mach number, 6 and bluntness effect. 7 With regard to a waverider, an attached shock wave along the leading edge prevents the spillage of the high-pressure flow from the lower surface to upper surface.…”

Section: Introductionmentioning

confidence: 99%

Effect of upper surface shape on waverider performances

Liu

Tian

Bai

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Waveriders are of high lift-to-drag (L/D) ratio in hypersonic states; however, low volume of loading limits its application in practical engineering significantly. Raising the upper surface is a method to increase the volume space for waveriders, and this article studies the effect of the upper surface shape on the aerodynamic performances based on a single swept waverider configuration. Cubic polynomials were employed to construct the upper surface to replace the freestream-traced surface, and 2 parameters, the trailing edge thickness and inclination angle of head, were extracted as design variables. Analyzing the flow field using computational fluid dynamics techniques, raising the upper surface only had effect on the aerodynamic performance from the upper surface, but nearly no effect on the lower surface, and thus the design of upper and lower surfaces can be decoupled. As the trailing edge thickness and inclination angle of head increase, the volume of waveriders grows rapidly, while the loss in L/D ratio is limited. Compared with expanding the lower surface, raising the upper surface yielded better aerodynamic performances. The results indicate that raising the upper surface is a feasible and efficient approach to increase the loading volume of the waverider and hence promote its application in engineering.

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Low speed longitudinal aerodynamic, static stability and performance analysis of a hypersonic waverider

Cited by 14 publications

References 32 publications

A Generic Model for Benchmark Aerodynamic Analysis of Fifth-Generation High-Performance Aircraft

A Generic Model for Benchmark Aerodynamic Analysis of Fifth-Generation High-Performance Aircraft

Research on the Performance of Slender Aircraft with Flare-Stabilized-Skirt

Effect of upper surface shape on waverider performances

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