CFD analysis and wind tunnel experiments of hypersonic shock-shock interaction heating for two hemisphere cylinder problem

Yamamoto, Y.; Nagai, Satoshi; Koyama, Tadao; Tsuda, S.; Hirabayashi, Noriaki; Hozumi, Kouichi

doi:10.2514/6.2002-217

Cited by 14 publications

(2 citation statements)

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“…The surface heat transfer rates computed by different fluxes from each group are also compared with theory. In contrast to [4], we used a grid not aligned with a theoretical shock shape, because shock alignment is practically impossible, for instance, in shock-shock interacting problems [34][35][36][37][38]. For the shock-aligned grid cases (see [39]).…”

Section: Hypersonic Heating Test: Hypersonicmentioning

confidence: 99%

Evaluation of Euler Fluxes for Hypersonic Heating Computations

et al. 2010

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In hypersonic flow computations, it is a key issue to predict surface heating accurately, though this is still challenging because there always are possibilities of resulting in anomalous solutions. In this paper, three properties for flux functions are proposed: 1) shock stability/robustness, 2) conservation of total enthalpy, and 3) resolving boundary layer. Then, numerical experiments are performed for widely used or recently developed flux functions, and these fluxes are categorized into five major groups based on how they satisfy the three properties. These tests reveal that no flux function investigated here possesses all the three properties. In particular, the first one is not satisfied by any flux functions, including flux-vector-splittings. Finally, contributions of those properties are compared in a two-dimensional, viscous, hypersonic blunt-body problem. Results showed that the first and the third properties are crucial, and the second one is preferred to predict hypersonic heating. A group of flux functions that best satisfies these properties is suggested, and they are recommended either to be used or designed for hypersonic heating computations.

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Section: Hypersonic Heating Test: Hypersonicmentioning

confidence: 99%

Evaluation of Euler Fluxes for Hypersonic Heating Computations

et al. 2010

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“…The last geometric test case is a 2-body 'Two Stage To Orbit' (TSTO) test case initially created by Yamamoto et al [31]. We add in a simple 27 background grid to fill out a larger domain.…”

Section: Connectivity Robustnessmentioning

confidence: 99%

A parallel direct cut algorithm for high-order overset methods with application to a spinning golf ball

Crabill

Witherden

Jameson

2018

Journal of Computational Physics

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Overset methods are commonly employed to enable the effective simulation of problems involving complex geometries and moving objects such as rotorcraft. This paper presents a novel overset domain connectivity algorithm based upon the direct cut approach suitable for use with GPU-accelerated solvers on high-order curved grids. In contrast to previous methods it is capable of exploiting the highly data-parallel nature of modern accelerators. Further, the approach is also substantially more efficient at handling the curved grids which arise within the context of high-order methods. An implementation of this new algorithm is presented and combined with a high-order fluid dynamics code. The algorithm is validated against several benchmark problems, including flow over a spinning golf ball at a Reynolds number of 150,000.problems of engineering interest, including entire rotorcraft configurations with relative motion between one or more rotors in addition to a fixed fuselage.One of the many advantages of this approach, compared with say deforming grids, is that it is possible to employ multiple solvers: an unstructured near-body solver to allow for easier mesh generation around each body, and a high-order Cartesian off-body solver with adaptive mesh refinement (AMR) for speed and simplicity. In most production codes used for complex geometries, such as the CREATE-AV HELIOS software [2], the near-body solvers are typically 2nd or 3rd order accurate in space. Higherorder near-body solvers are available, but only for (multi-block) structured grids currently, such as with the OVERFLOW code using 5th order accurate finite differences [3,4]. For the best possible performance, accuracy, and applicability to a wide range of complex geometries, however, a higherorder unstructured near-body solver is preferable. As shown by Wissink [5] and by Nastase et al. [6], without a high-order near body solver, vortical structures and other flow features incur high amounts of diffusion before (or while) passing into the high-order off-body solver, causing a large increase in error.High order methods have a number of attractive attributes. Not only are they less dissipative, enabling the simulation of vortex-dominated flows with fewer degrees of freedom than a lower-order method, but they have also been shown to give remarkably good results when used to perform implicit large eddy simulations (ILES) and direct numerical simulations (DNS) [7,8]. Popular examples of high-order schemes for unstructured grids include the discontinuous Galerkin finite element method, first introduced by Reed and Hill [9], and spectral difference (SD) methods originally proposed under the moniker 'staggered-grid Chebyshev multidomain methods' by Kopriva and Kolias in 1996 [10] and later popularized by Sun et al. [11]. In 2007 Huynh proposed the flux reconstruction (FR) approach [12]; a unifying framework for high-order schemes for unstructured grids that encompasses both the nodal DG schemes of Hesthaven and Warburton [13] and, at least for a linear flux functi...

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Aerodynamic Interference Reduction Using Aerospike for Two-Stage Reusable Launch Vehicle

Liao

Song

et al. 2023

J. Aerosp. Eng.

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CFD analysis and wind tunnel experiments of hypersonic shock-shock interaction heating for two hemisphere cylinder problem

Cited by 14 publications

References 1 publication

Evaluation of Euler Fluxes for Hypersonic Heating Computations

Evaluation of Euler Fluxes for Hypersonic Heating Computations

A parallel direct cut algorithm for high-order overset methods with application to a spinning golf ball

Aerodynamic Interference Reduction Using Aerospike for Two-Stage Reusable Launch Vehicle

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