A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Le, Duan; Wang, Xiaowen; Zhong, Xiaolin

doi:10.1016/j.jcp.2010.06.008

Cited by 78 publications

(47 citation statements)

References 56 publications

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“…It should also be noted that the excited second-mode instability does not depend on the disturbance source as long as the disturbance is small and in the linear region. For example, the second-mode instability range matches in [7] and [18], although different disturbance sources (blowing and suction, pure mode S∕F, and a pulse), are imposed into the same freestream conditions. In the current simulation, disturbances of 0.001% of the corresponding freestream values are used and the experiment is performed in a quiet tunnel.…”

Section: B Experiments and Simulation Comparisonmentioning

confidence: 99%

“…However, the mechanisms were not investigated. At the same time, Duan et al [7] from University of California, Los Angeles (UCLA) reported that a 2-D roughness element can damp disturbances if the element is placed downstream of the location where the slow hypersonic boundarylayer mode (mode S) and fast hypersonic boundary-layer mode (mode F) have the same phase velocity (the synchronization location). The details of the work by the UCLA group will be discussed in the next paragraph.…”

Section: Introductionmentioning

confidence: 99%

“…The new method was then applied to simulating finite roughness elements in a hypersonic boundary layer at Mach 5.92 [7,14]. Different from the wavy wall idea, as in [5] and [10], they found that the relative location of the 2-D roughness element and the synchronization location plays an important role [7]. The synchronization location is the point where the mode S and mode F disturbance have the same phase velocity.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Second Mode Suppression in Hypersonic Boundary Layer by Roughness: Design and Experiments

Fong¹,

Wang²,

Huang³

et al. 2015

AIAA Journal

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Section: B Experiments and Simulation Comparisonmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Second Mode Suppression in Hypersonic Boundary Layer by Roughness: Design and Experiments

Fong¹,

Wang²,

Huang³

et al. 2015

AIAA Journal

Self Cite

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“…This paper presents and validates a less conventional FSI method, in which a higher-order immersed boundary method for the compressible Navier-Stokes equations is coupled with a structural finite element method (FEM). Immersed Boundary Methods (IBMs) have been developed for many years and have appeared in various forms since they were first introduced by Peskin 3, 4 (see for example Goldstein et al, 5 LeVeque and Li, 6 Wiegmann and Bube, 7 Linnick and Fasel, 8 Johansen and Collela, 9 Mittal and Iaccarino, 10 Zhong, 11 Duan et al 12 and many others). These methods were first introduced as a nontraditional approach for numerically solving initial/boundary-value problems for complex geometries on Cartesian meshes and have matured to become increasingly important for a wide range of applications.…”

Section: Introductionmentioning

confidence: 99%

An Immersed Boundary Method for Solving the Compressible Navier-Stokes Equations with Fluid-Structure Interaction

Brehm

Barad

Kiris

2016

34th AIAA Applied Aerodynamics Conference

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An immersed boundary method for the compressible Navier-Stokes equation and the additional infrastructure that is needed to solve moving boundary problems and fully coupled fluid-structure interaction is described. All the methods described in this paper were implemented in NASA's LAVA solver framework. The underlying immersed boundary method is based on the locally stabilized immersed boundary method that was previously introduced by the authors. In the present paper this method is extended to account for all aspects that are involved for fluid structure interaction simulations, such as fast geometry queries and stencil computations, the treatment of freshly cleared cells, and the coupling of the computational fluid dynamics solver with a linear structural finite element method. The current approach is validated for moving boundary problems with prescribed body motion and fully coupled fluid structure interaction problems in 2D and 3D. As part of the validation procedure, results from the second AIAA aeroelastic prediction workshop are also presented. The current paper is regarded as a proof of concept study, while more advanced methods for fluid structure interaction are currently being investigated, such as geometric and material nonlinearities, and advanced coupling approaches.

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“…It is natural that influence of roughness on the convective instability of mode S need to be examined first to investigate the cause of delaying transition. Duan et al 4,5 and Fong et al 6 investigated roughness effect on instability of mode S by using direct numerical simulations (DNS). Their DNS studies showed that the roughness located at the downstream of synchronization point can stabilize mode S. Although they imposed mode S at the inflow boundary and focused on its downstream evolution, it is possible in DNS study that the other mechanisms other than the convective instability of mode S can be involved due to roughness.…”

Section: Introductionmentioning

confidence: 99%

Study on Stabilization and Destabilization Effect of a Smooth Hump in Hypersonic Boundary Layers by PSE

Park

2013

43rd Fluid Dynamics Conference

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Effect of a two-dimensional smooth hump on linear instability of hypersonic boundary layer is studied. Parabolized stability equations (PSE) is employed to analyze the linear evolution of mode S over a hump in Mach 4.5 and 5.92 flat plate and Mach 7.1 sharp cone boundary layers. Mean flow for stability analysis is obtained by solving the parabolized Navier-Stokes (PNS) equations. Hump with height smaller than local boundary layer thickness is used. The case of flat plate and sharp cone without the hump are also studied to provide comparable data. For flat plate boundary layers, destabilization and stabilization effect of hump located at upstream and downstream of synchronization point are confirmed. Results of parametric studies to examine the effect of hump height, location, etc. are also given. For sharp cone boundary layer, stabilization influence of hump is also identified for a specific range of frequency. Stabilization influence of hump on convective instability of mode S is found to be a possible cause of previous experimental observations of delaying transition in hypersonic boundary layers. Nomenclature b = hump half width c = phase speed f = physical frequency F = non-dimensional frequency h = hump height L = streamwise distance from leading dege to hump center location M = Mach number N = N-factor R = Reynolds number based on boundary layer length scale Re = unit Reynolds number Re L = Reynolds number based on L δ = boundary layer length scale θ c = cone half angle ω = angular frequency

show abstract

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Cited by 78 publications

References 56 publications

Second Mode Suppression in Hypersonic Boundary Layer by Roughness: Design and Experiments

Second Mode Suppression in Hypersonic Boundary Layer by Roughness: Design and Experiments

An Immersed Boundary Method for Solving the Compressible Navier-Stokes Equations with Fluid-Structure Interaction

Study on Stabilization and Destabilization Effect of a Smooth Hump in Hypersonic Boundary Layers by PSE

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