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In this paper we numerically evaluate the recently developed Aoki et al. slip and jump conditions in high-speed rarefied gas flows for the first time. These slip and jump conditions are developed to be employed with the Navier–Stokes–Fourier equations. They were derived based on the Boltzmann equation with the first order Chapman–Enskog solution, and the analysis of the Knudsen layer. Four aerodynamic configurations are selected for a comprehensive evaluation of these conditions such as sharp-leading-edge flat plate, vertical plate, wedge and circular cylinder in cross-flow with the Knudsen number varying from 0.004 to 0.07, and argon as the working gas. The simulation results using the Aoki et al. boundary conditions show suitable agreement with the DSMC data for slip velocity and surface gas temperature. The accuracy of these boundary conditions is superior to the conventional Maxwell, Smoluchowski and Le boundary conditions. [ABSTRACT FROM AUTHOR]

Flow regimes through micro/nano nozzles experience the continuum behavior as well as the rarefied condition. The occurrence of broad rarefaction regimes due to unique geometry/flow conditions makes the particle-based simulation of micro/nano nozzles computationally expensive. Therefore, the primary aim of the present study is to implement the Simplified Bernoulli trials (SBT) collision algorithm in place of the conventional “No-Time-Counter” scheme in the direct simulation Monte Carlo (DSMC) method, thus reducing the required particle number. We show that the SBT scheme employed on the proper number of grid cells could reduce the computational costs and memory of micro/nano nozzle flow simulations. We also investigated the physical behavior of gas flows in micro/nano nozzles. We report the bimodal behavior of the velocity, temperature and Mach number at the throat at lower Knudsen numbers and the occurrence of Mach < 1 in the throat. We also considered back pressure effects on the flow field and the impact of gas species on the micro/nano nozzle performance. We identified an efficiency reduction due to rarefaction and improvements of the micro/nano nozzle performance due to increasing of the throat dimension. Performance reduction at the nanoscale is also discussed. [ABSTRACT FROM AUTHOR]

The NACA 0012 airfoil and the sharp 25–55-deg biconic cases are usually considered in evaluating the accuracy of new forms of velocity slip and temperature jump wall boundary conditions in the Navier–Stokes–Fourier equations. These cases have been investigated by many researchers in previous works with the first order Maxwell slip and Smoluchowski jump boundary conditions. Recently, we proposed a new form of the second order temperature jump for simulating rarefied gas flows and obtained accurate results for low-speed microflows. The current work is an extension of our previous CFD work where we applied both the second order velocity slip condition and the second order temperature jump boundary condition in new forms to simulate rarefied external gas flows for these cases. The second order boundary conditions are implemented into the rhoCentralFoam solver in the OpenFOAM software. The NACA 0012 airfoil case is investigated with angles-of-attack of 0 and 10 degrees and Mach numbers of 0.8 and 2. The sharp 25–55-deg biconic case is simulated at Mach of 15.6. The simulation results obtained for the NACA 0012 airfoil show that the combination of the second order slip/jump boundary conditions gives suitable agreements with DSMC for surface gas temperature and drag coefficients in comparison with those of the first order conditions. However, the results of the biconic case figure out that the second order conditions are not superior to the first order conditions. [ABSTRACT FROM AUTHOR]