Role of solution reconstruction in hypersonic viscous computations using a sharp interface immersed boundary method

Brahmachary, Shuvayan; Natarajan, Ganesh; Kulkarni, Vinayak; Sahoo, Niranjan; Ashok, V.; Kumar, Vinod

doi:10.1103/physreve.103.043302

Cited by 9 publications

(7 citation statements)

References 28 publications

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“…This is expected due to the aforementioned shortcomings in its nonconservative IBM. A similar underprediction has also been reported in literature by Brahmachary et al [11], where the issue has been linked to the reconstruction of temperature by linear interpolation. We would like to remark that since INCA is also following a similar approach for reconstructing these variables, the larger source of error is still attributed to the nonconservative nature of the IBM.…”

Section: Inert Isothermal Wallsupporting

confidence: 84%

“…A promising alternative is the use of adaptive mesh refinement techniques based on Cartesian grids with immersed boundary methods (IBM), which offer a relatively straight-forward implementation of high-order schemes. There has been a recently growing interest in IBM solvers [7][8][9][10][11], mainly for their potential for complex and deforming geometries. Especially for boundaries under motion, immersed boundary methods are much more robust and efficient compared to the body-conformal approach.…”

Section: Introductionmentioning

confidence: 99%

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Verification and Validation of Immersed Boundary Solvers for Hypersonic Flows with Gas-Surface Interactions

Başkaya

Capriati

Ninni

et al. 2022

AIAA AVIATION 2022 Forum

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During atmospheric entry, the flow environment around capsules or space debris is characterized by complex fluid thermochemistry and gas-surface interactions (GSI). Computational fluid dynamics (CFD) simulations of these conditions are crucial in the design process of such objects. A promising approach for the simulation of complex geometries is the use of immersed boundary methods (IBM) and adaptive mesh refinement techniques (AMR). These methods offer reliable and efficient mesh generation and adaptation with minimal user intervention. To that end, this paper presents the recent developments of two IBM-AMR solvers coupled with the same external thermochemistry library for the accurate modelling of such complex flows including GSI. Several verification and validation cases are presented, which demonstrate the performance of the solvers. Results are analyzed in comparison with a body-conforming solver that uses the same thermochemistry library to achieve a consistent assessment of the underlying numerical methods. A good agreement between all the solvers is indicated with certain discrepancies arising due to the differences in surface treatments.

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Section: Inert Isothermal Wallsupporting

confidence: 84%

Section: Introductionmentioning

confidence: 99%

Verification and Validation of Immersed Boundary Solvers for Hypersonic Flows with Gas-Surface Interactions

Başkaya

Capriati

Ninni

et al. 2022

AIAA AVIATION 2022 Forum

View full text Add to dashboard Cite

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“…Numerical simulations of hypersonic flow past a cylinder are conducted. The inflow Mach number M ∞ is 8.03, and the Reynolds number Re based on the diameter D = 0.0381 m is 3.67 × 10 5 , and this condition is the same as the numerical simulation by Brahmachary et al (2021). The upstream temperature T ∞ is 124.94 K. The temperature T w of the isothermal wall is 294.44 K. The chemical reactions are ignored since frozen flow is assumed.…”

Section: Numerical Simulations Of the Hypersonic Flow Past A Cylindermentioning

confidence: 99%

“…The grid conditions are ∆x = 1.4 × 10 −5 m and ∆x = 0.7 × 10 −5 m, and the cell Reynolds numbers Re cell are Re cell = 67.4 and 33.7. The ∆x = 1.4 × 10 −5 m condition is equivalent to the near-wall grid resolution of the adapted unstructured Cartesian grid used in Brahmachary et al (2021).…”

Section: Numerical Simulations Of the Hypersonic Flow Past A Cylindermentioning

confidence: 99%

“…In the numerical simulation of the flow around a supersonic cylinder, Brahmachary et al (2021) reported underestimations of the wall heat flux at the stagnation point and the temperature distribution by the immersed boundary method. These underestimations are discussed in detail, and the authors conclude that the underestimations are not provided by…”

Section: Introductionmentioning

confidence: 99%

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Wall heat flux estimation using the Cartesian cut-cell method

TAKEDA,

BABA,

UENO

2023

JFST

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The Cartesian cut-cell method evaluates wall-fluid interactions by using the fluxes through a wall. This wall treatment by the Cartesian cut-cell method is expected to overcome the mass and energy conservation problems of the immersed boundary method. A wall flux evaluation using the image point is proposed in this study to avoid volume center estimation. The Cartesian cut-cell method that uses the proposed wall flux evaluation is validated by the numerical simulations of supersonic flows past simple shapes. In the numerical simulations of the supersonic flow past a cylinder with an isothermal wall, the shorter displacement d IP of the image point from the wall provided a better estimation of the wall heat flux. Furthermore, the wall heat flux distributions and the amount of heat converged with grid refinement. In the numerical simulations of the supersonic flow past a wedge, the minimum grid resolution of the Cartesian cut-cell method for wall flux estimation was suggested. Furthermore, the results of the isothermal wall condition, the adiabatic wall condition, and the inviscid condition were compared.

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Impact of energy deposition as active flow control on scramjet inlet performance using Immersed Boundary Method

Pathak,

Khare,

Kulkarni

2024

Acta Astronautica

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Role of solution reconstruction in hypersonic viscous computations using a sharp interface immersed boundary method

Cited by 9 publications

References 28 publications

Verification and Validation of Immersed Boundary Solvers for Hypersonic Flows with Gas-Surface Interactions

Verification and Validation of Immersed Boundary Solvers for Hypersonic Flows with Gas-Surface Interactions

Wall heat flux estimation using the Cartesian cut-cell method

Impact of energy deposition as active flow control on scramjet inlet performance using Immersed Boundary Method

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