The objective of the study is to assess the accuracy of kinetic schemes in resolving the internal structure of the shock waves. Two kinetic schemes were used, a gas kinetic BGK scheme and the direct integration of the Boltzmann equation. The argon hard sphere collision model was considered for freestream Mach numbers ranging from 1.2 to 10. The results from the calculations of the direct integration of Boltzmann equations of Ohwada were used as benchmark for Mach 1.2, 2, and 3 shock waves. The results from the direct integration solvers matched reasonably well. Agreement from gas kinetic BGK scheme at the low Mach number was good, but at higher Mach number the starting jump location was missed. A study of the velocity grid requirements for ...
The structure of a plane shock wave is discussed and the expected range of applicability of the Navi...
AFIT/GAE/ENY/09-M02 The Unified Flow Solver, a hybrid continuum-rarefied code, is used to investi-ga...
Shock tube experiments are a key method of reproducing the flow conditions encountered by hypersonic...
The Bhatnagar-Gross-Krook (BGK) collision model is an approximation to the Boltzmann’s equation. Bas...
The structure of gas-dynamic shock waves is of interest in hypersonic flow studies and also constitu...
In this thesis the extension of Xu's BGK scheme with the inclusion of non-equilibrium state to descr...
The gas-kinetic scheme (GKS) is a finite-volume method in which the fluxes are constructed from the ...
A formulation for the shock wave structure is devised by viewing the transition as a phenomenon in ...
Accurately computing the inner structure of normal shock waves or oblique shock waves is crucial for...
Accurately computing the inner structure of normal shock waves or oblique shock waves is crucial for...
'Best' solutions for the shock-structure problem are obtained by solving the Boltzmann equation for ...
Many problems arising in the aerodynamic design of aerospace vehicles require the numerical solution...
This paper extends the gas-kinetic BGK-type scheme to low Mach number flows, and thus shows that inc...
The structure of a plane shock wave is discussed and the expected range of applicability of the Navi...
Abstract. Progress in computer hardware and improvement of numerical methods made solution of the Bo...
The structure of a plane shock wave is discussed and the expected range of applicability of the Navi...
AFIT/GAE/ENY/09-M02 The Unified Flow Solver, a hybrid continuum-rarefied code, is used to investi-ga...
Shock tube experiments are a key method of reproducing the flow conditions encountered by hypersonic...
The Bhatnagar-Gross-Krook (BGK) collision model is an approximation to the Boltzmann’s equation. Bas...
The structure of gas-dynamic shock waves is of interest in hypersonic flow studies and also constitu...
In this thesis the extension of Xu's BGK scheme with the inclusion of non-equilibrium state to descr...
The gas-kinetic scheme (GKS) is a finite-volume method in which the fluxes are constructed from the ...
A formulation for the shock wave structure is devised by viewing the transition as a phenomenon in ...
Accurately computing the inner structure of normal shock waves or oblique shock waves is crucial for...
Accurately computing the inner structure of normal shock waves or oblique shock waves is crucial for...
'Best' solutions for the shock-structure problem are obtained by solving the Boltzmann equation for ...
Many problems arising in the aerodynamic design of aerospace vehicles require the numerical solution...
This paper extends the gas-kinetic BGK-type scheme to low Mach number flows, and thus shows that inc...
The structure of a plane shock wave is discussed and the expected range of applicability of the Navi...
Abstract. Progress in computer hardware and improvement of numerical methods made solution of the Bo...
The structure of a plane shock wave is discussed and the expected range of applicability of the Navi...
AFIT/GAE/ENY/09-M02 The Unified Flow Solver, a hybrid continuum-rarefied code, is used to investi-ga...
Shock tube experiments are a key method of reproducing the flow conditions encountered by hypersonic...