2018 AIAA Aerospace Sciences Meeting 2018
DOI: 10.2514/6.2018-0062
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A physics-based shock capturing method for unsteady laminar and turbulent flows

Abstract: We present a shock capturing method for unsteady laminar and turbulent flows. The proposed approach relies on physical principles to increase selected transport coefficients and resolve unstable sharp features, such as shock waves and strong thermal and shear gradients, over the smallest distance allowed by the discretization. In particular, we devise various sensors to detect when the shear viscosity, bulk viscosity and thermal conductivity of the fluid do not suffice to stabilize the numerical solution. In s… Show more

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Cited by 28 publications
(22 citation statements)
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References 38 publications
(51 reference statements)
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“…In this approach, shock waves are stabilised by correcting the diffusive flux in equation ( 1) using the physicsbased approach proposed in [51]. This methodology, stemming from the work of Von Neumann and Richtmyer [132] and later considered in [35,75,76], relies on defining the diffusive flux as a combination of the physical flux G with an additional numerical contribution G * .…”
Section: Physics-based Shock Capturingmentioning
confidence: 99%
See 3 more Smart Citations
“…In this approach, shock waves are stabilised by correcting the diffusive flux in equation ( 1) using the physicsbased approach proposed in [51]. This methodology, stemming from the work of Von Neumann and Richtmyer [132] and later considered in [35,75,76], relies on defining the diffusive flux as a combination of the physical flux G with an additional numerical contribution G * .…”
Section: Physics-based Shock Capturingmentioning
confidence: 99%
“…First, a dilatation-based shock sensor [51,87], which identifies the regions of high compression, is defined as…”
Section: Physics-based Shock Capturingmentioning
confidence: 99%
See 2 more Smart Citations
“…Third-order HDG and DIRK (3,3) schemes are used for the discretization. The details of the simulation setup are presented in [50]. Figure 9 shows 2D slices of the time-averaged (left) and instantaneous (right) pressure, temperature and Mach number fields.…”
Section: Transonic Flow Over the T106c Low-pressure Turbinementioning
confidence: 99%