### Abstract

A low-diffusive node-pair formulation of conservation laws is here reformulated in terms of a Boltzmann based kinetic scheme to address nonequilibrium flows up to the continuum-transitional regime. The ability to address flows for which the continuumlimit is no longer valid comes from the adoption of an improved formula for themean collision time of themolecules of the gas. From a numerical point of view, differently from particle based methods like DSMC, a macroscopic set of equations is solved for the conserved variables, and the kinetic theory of gases is used to compute the numerical flux along the boundary of each control volume for the flow conditions under investigation. As a result, a unified formula for any flow conditions from continuum up to the transitional regime, in the context of an edge-based scheme for hybrid grids is here presented. Exemplary shock structure computations and different transitional flows around a cylinder are considered here to evaluate the performance of the present scheme.

Language | English |
---|---|

Title of host publication | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 |

DOIs | |

Publication status | Published - 1 Dec 2011 |

Event | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 - San Francisco, CA, United States Duration: 11 Apr 2011 → 14 Apr 2011 |

### Conference

Conference | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 |
---|---|

Country | United States |

City | San Francisco, CA |

Period | 11/04/11 → 14/04/11 |

### Fingerprint

### Keywords

- numerical simulation
- hypersonic transitional flows
- kinetic node-pair approach
- kinetic theory of gases
- computational fluid dynamics
- numerical methods
- transition flow
- non-equilibrium flows
- shock structures

### Cite this

*17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011*https://doi.org/10.2514/6.2011-2219

}

*17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011.*17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011, San Francisco, CA, United States, 11/04/11. https://doi.org/10.2514/6.2011-2219

**Numerical simulation of hypersonic transitional flows by means of a kinetic node-pair approach.** / Fossati, M.; Vigevano, L.; Xu, K.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

TY - GEN

T1 - Numerical simulation of hypersonic transitional flows by means of a kinetic node-pair approach

AU - Fossati, M.

AU - Vigevano, L.

AU - Xu, K.

PY - 2011/12/1

Y1 - 2011/12/1

N2 - A low-diffusive node-pair formulation of conservation laws is here reformulated in terms of a Boltzmann based kinetic scheme to address nonequilibrium flows up to the continuum-transitional regime. The ability to address flows for which the continuumlimit is no longer valid comes from the adoption of an improved formula for themean collision time of themolecules of the gas. From a numerical point of view, differently from particle based methods like DSMC, a macroscopic set of equations is solved for the conserved variables, and the kinetic theory of gases is used to compute the numerical flux along the boundary of each control volume for the flow conditions under investigation. As a result, a unified formula for any flow conditions from continuum up to the transitional regime, in the context of an edge-based scheme for hybrid grids is here presented. Exemplary shock structure computations and different transitional flows around a cylinder are considered here to evaluate the performance of the present scheme.

AB - A low-diffusive node-pair formulation of conservation laws is here reformulated in terms of a Boltzmann based kinetic scheme to address nonequilibrium flows up to the continuum-transitional regime. The ability to address flows for which the continuumlimit is no longer valid comes from the adoption of an improved formula for themean collision time of themolecules of the gas. From a numerical point of view, differently from particle based methods like DSMC, a macroscopic set of equations is solved for the conserved variables, and the kinetic theory of gases is used to compute the numerical flux along the boundary of each control volume for the flow conditions under investigation. As a result, a unified formula for any flow conditions from continuum up to the transitional regime, in the context of an edge-based scheme for hybrid grids is here presented. Exemplary shock structure computations and different transitional flows around a cylinder are considered here to evaluate the performance of the present scheme.

KW - numerical simulation

KW - hypersonic transitional flows

KW - kinetic node-pair approach

KW - kinetic theory of gases

KW - computational fluid dynamics

KW - numerical methods

KW - transition flow

KW - non-equilibrium flows

KW - shock structures

UR - http://www.scopus.com/inward/record.url?scp=84881284401&partnerID=8YFLogxK

U2 - 10.2514/6.2011-2219

DO - 10.2514/6.2011-2219

M3 - Conference contribution book

SN - 9781600869426

BT - 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011

ER -