Computational Fluid Dynamics Study of Optimized Hypersonic Leading Edge Geometries

Hinman, W. Schuyler; Johansen, Craig T.; Rodi, Patrick E.

doi:10.2514/6.2015-3509

Cited by 4 publications

(2 citation statements)

References 7 publications

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“…Convective heat-flux databases for the un-swept leading edge region of the vehicles (where the heat flux is expected to be the highest) are generated using the Newton-Kays model presented in [16] and adopted in [17] for a rapid shape optimisation study.…”

Section: B Aerothermodynamicsmentioning

confidence: 99%

Integrated Shape and Trajectory Optimisation of Hypersonic Waveriders

Carvalho,

Mooij

2024

AIAA SCITECH 2024 Forum

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= Entry velocity (m/s) w 1 = Fuselage half width (m) w 2 = Wing semi-span (m) χ E = Entry heading angle (rad) I. Introduction and MotivationLarge satellite constellations are becoming a reality, and the growing number of spacecraft to be launched to orbits with different inclinations and altitudes raises the need for a highly flexible and frequently requested satellite launch service. It is in such conditions that a reusable concept becomes economically advantageous with respect to expendable systems, as noted in [1]. Despite their complexity and absence from the current launch vehicle market, reusable space-plane concepts are more flexible than their rocket counterparts. The superior control over the aerodynamic forces allows mission recall in case a payload problem is detected during ascent, and a larger number of landing sites becomes accessible when re-entering from a successful launch, reducing the turnaround time and costs.Landing flexibility is strongly driven by the lift-to-drag ratio at hypersonic speeds. Waveriders are a sub-class of lifting-bodies with lift-to-drag ratios that are superior to conventional hypersonic configurations, so they have the potential to become a competitive operational launch vehicle. Such idea was already pursued in the 1980s with the National Aero-Space Plane and its technology demonstrator project, the Rockwell X-30.However, pure waverider shapes are not realistic entry vehicles for a myriad of reasons. First, they rely on sharp leading edges, which have to be rounded off so that they can withstand the aerodynamic heat flux, an operation that inevitably degrades the aerodynamic performance at hypersonic speeds. A second issue is that waveriders are designed for specific flight conditions, while in a re-entry scenario they are constantly flying at off-design conditions. Without intelligent vehicle design, this can result in the degradation of the flight performance and bring complications to the thermal protection system design. Another concern is the lack of aerodynamic surfaces to trim and control the vehicle.These concerns motivate the development of a modified waverider shape and of a framework to understand how its design should be modified and optimised, considering the trade-off between heat load and flight range that is commonly made for re-entry missions. Shape variability leads to variability in the achievable and optimal re-entry flight profiles. To respect such coupling, a joint shape and trajectory optimisation approach will be adopted. This approach will not be applied to an operational vehicle, but rather to a down-sized technology demonstrator, which is likely needed to mitigate development risks and costs. The scope of the research will be limited to the hypersonic flight regime, as it is typically the most demanding segment of the entry [2]. II. Methodology A. Vehicle DesignFirst, a baseline wedge-derived waverider will be established: a caret wing [3] split in half in the symmetry plane and then joined together by a wedge that acts as a fuselage, as shown i...

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Section: B Aerothermodynamicsmentioning

confidence: 99%

Integrated Shape and Trajectory Optimisation of Hypersonic Waveriders

Carvalho,

Mooij

2024

AIAA SCITECH 2024 Forum

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“…In a supersonic flow, the residence time of the flow is very short, but the aerodynamic load is high, so it is not possible to control the flow through mechanically moving components, as in a subsonic region. At the early age of cutting-edge design optimization studies [1][2][3], fixed structures like aero spikes [4][5][6][7] were suggested. However, the structure has other problems, like excessive thermal loads at the tip, additional loads at off-design operations, and induced moment during the maneuvering flight.…”

Section: Introductionmentioning

confidence: 99%

Influence of Laser Energy Deposition Conditions on the Drag of A Sphere in Supersonic Flow

Kim

Lee

2019

Energies

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In the present study, a two-dimensional axisymmetry unsteady numerical simulation that implements high-frequency laser energy deposition was performed to understand its influence on drag reduction in supersonic flow. The energy deposition was modeled as the increase of the temperature inside the focal region. The drag reduction characteristics were investigated by changing the frequency of the deposition, the distance between the focus of the deposition and the body, and the power of the laser. The results showed that drag could be reduced by 60% when there was a single energy deposition. As the operating frequency increased, up to 70% drag reduction was obtained. When the laser energy was deposed more frequently than 75 kHz, the normalized drag converged regardless of the deposition scenario, which resulted from the multiple interactions between the blast wave and the reflected shock. A similar tendency was found from the results of various focal distances. According to the results of this study on the effect of the deposition energy, it is expected to achieve the same effect as with low energy by increasing the frequency of the deposition.

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Effect of particle momentum transfer on an oblique-shock-wave/laminar-boundary-layer interaction

Teh

Johansen

2016

Acta Astronautica

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Computational Fluid Dynamics Study of Optimized Hypersonic Leading Edge Geometries

Cited by 4 publications

References 7 publications

Integrated Shape and Trajectory Optimisation of Hypersonic Waveriders

Integrated Shape and Trajectory Optimisation of Hypersonic Waveriders

Influence of Laser Energy Deposition Conditions on the Drag of A Sphere in Supersonic Flow

Effect of particle momentum transfer on an oblique-shock-wave/laminar-boundary-layer interaction

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