On the use of immersed boundary methods for shock/obstacle interactions

Chaudhuri, A.; Hadjadj, A.; Chinnayya, A.

doi:10.1016/j.jcp.2010.11.016

Cited by 142 publications

(70 citation statements)

References 35 publications

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“…The discontinuous inviscid flow problem was Sod's shock tube problem 38 which was chosen to test the dissipative discontinuity-capturing advection schemes. The viscous flow example with multiple shocks and vortices was a viscous version of the inviscid Mach 3.5 2-D cylinder in crossflow benchmark problem described by Chuadhuri et al 40 which was chosen to test the discontinuity sensors and the hybrid-advection schemes ability to capture complex shock/vortex interactions in a temporally evolving viscous flow. The discontinuous turbulent flow containing features found in a high-speed propulsion flowpath was supersonic cavity-ramp experiment of Settles et al…”

Section: Benchmark Problemsmentioning

confidence: 99%

“…Furthermore, although the HLLC approximate Riemann solver was found to b preferable to the LLF approximate Riemann solver, LLF continued to be considered because it is commonly used with WENO schemes. 40 was simulated to test the ability of selected hybrid-advection schemes to resolve a flow rich in shock-shock and shock-vortex interactions. These types of interactions are also of particular interest when computing hypersonic propulsion flow paths.…”

Section: B Discontinuous Flow Benchmarks B1 Sods 1-d Shock Tubementioning

confidence: 99%

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Low-Dissipation Advection Schemes Designed for Large Eddy Simulations of Hypersonic Propulsion Systems

White

Baurle²,

Fisher³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The 2nd-order upwind inviscid flux scheme implemented in the multi-block, structured grid, cell centered, finite volume, high-speed reacting flow code VULCAN has been modified to reduce numerical dissipation. This modification was motivated by the desire to improve the codes ability to perform large eddy simulations. The reduction in dissipation was accomplished through a hybridization of non-dissipative and dissipative discontinuity-capturing advection schemes that reduces numerical dissipation while maintaining the ability to capture shocks. A methodology for constructing hybrid-advection schemes that blends nondissipative fluxes consisting of linear combinations of divergence and product rule forms discretized using 4th-order symmetric operators, with dissipative, 3rd-or 4th -order reconstruction based upwind flux schemes was developed and implemented. A series of benchmark problems with increasing spatial and fluid dynamical complexity were utilized to examine the ability of the candidate schemes to resolve and propagate structures typical of turbulent flow, their discontinuity capturing capability and their robustness. A realistic geometry typical of a high-speed propulsion system flowpath was computed using the most promising of the examined schemes and was compared with available experimental data to demonstrate simulation fidelity. Nomenclature

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Section: Benchmark Problemsmentioning

confidence: 99%

Section: B Discontinuous Flow Benchmarks B1 Sods 1-d Shock Tubementioning

confidence: 99%

Low-Dissipation Advection Schemes Designed for Large Eddy Simulations of Hypersonic Propulsion Systems

White

Baurle²,

Fisher³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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show abstract

“…Recently, the Cartesian grid methods have become very popular in computational fluid dynamics (see [1][2][3][4][5][6][7][8][9][10][11] and their references), because such methods do not suffer from the complex grid generation and grid management requirements which are inherent in other methods, and also these methods are easily extended to high order numerical schemes. Conceptually, the Cartesian grid approach is much simpler to be implemented than other grid methods.…”

Section: Introductionmentioning

confidence: 99%

Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock

Liu

Qiu

Goman

et al. 2016

Numer. Math. Theory Methods Appl.

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Abstract. In order to suppress the failure of preserving positivity of density or pressure, a positivity-preserving limiter technique coupled with h-adaptive Runge-Kutta discontinuous Galerkin (RKDG) method is developed in this paper. Such a method is implemented to simulate flows with the large Mach number, strong shock/obstacle interactions and shock diffractions. The Cartesian grid with ghost cell immersed boundary method for arbitrarily complex geometries is also presented. This approach directly uses the cell solution polynomial of DG finite element space as the interpolation formula. The method is validated by the well documented test examples involving unsteady compressible flows through complex bodies over a large Mach numbers. The numerical results demonstrate the robustness and the versatility of the proposed approach.

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“…However, the majority of previously published IMBMs and their extensions considered incompressible fluid flow. For aeroacoustics and compressible fluid flow there are only few methods published, among them two for inviscid flow [3,4]. For noise propagation problems with prescribed noise sources Casalino et al [5] and Arina [6] as well as Cand et al [7] and Liu & Wu [8] presented IMBMs in the frequency and time domain, respectively.…”

Section: Introductionmentioning

confidence: 99%

The boundary data immersion method for compressible flows with application to aeroacoustics

Schlanderer

Weymouth

Sandberg

2017

Journal of Computational Physics

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This paper introduces a virtual boundary method for compressible viscous fluid flow that is capable of accurately representing moving bodies in flow and aeroacoustic simulations. The method is the compressible extension of the boundary data immersion method (BDIM, Maertens & Weymouth (2015)). The BDIM equations for the compressible Navier-Stokes equations are derived and the accuracy of the method for the hydrodynamic representation of solid bodies is demonstrated with challenging test cases, including a fully turbulent boundary layer flow and a supersonic instability wave. In addition we show that the compressible BDIM is able to accurately represent noise radiation from moving bodies and flow induced noise generation without any penalty in allowable time step.

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On the use of immersed boundary methods for shock/obstacle interactions

Cited by 142 publications

References 35 publications

Low-Dissipation Advection Schemes Designed for Large Eddy Simulations of Hypersonic Propulsion Systems

Low-Dissipation Advection Schemes Designed for Large Eddy Simulations of Hypersonic Propulsion Systems

Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock

The boundary data immersion method for compressible flows with application to aeroacoustics

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