This tutorial sets up simulations of thermally inductively coupled plasma at atmospheric pressure including effects of radiation heat transfer and conjugated flow/wall heat transfer. The tutorial employs the power of user subroutines to define the properties of the Argon gas found in the plasma tube. The relative permittivity, electrical conductivity, specific heat and thermal conductivity of the Argon gas are set using the user subroutines.
CFD-VisCART is an automated 3D viscous unstructured adaptive Cartesian grid generation tool for handling complex geometries. This tutorial describes the steps for generating a Cartesian grid with different mesh resolutions on various geometries using CFD-VisCart.
The steady state conductive heat transfer to the air-gap between infinitely long concentric thick-walled cylinders is modeled and compared with an analytical solution. This is a step-by-step guided introductory tutorial for setting up a heat transfer model in CFD-ACE+.
Lorentz force is the force
exerted on a charged particle in an electromagnetic field. Lorentz forces can be used
to control flow separation. In the example of flow separation over a
cylinder, the application of Lorentz force in a direction tangential to
the surface of the cylinder results in moving the separation point
rearward on the cylinder surface. This causes a reduction in the drag
over the cylinder.
In this tutorial, the geometry of a bent pipe is optimized. The bent section of the pipe must provide 90-degree change of direction for a fluid flowing through it. The objective is to determine the bend radius R that provides the minimal (optimal) pressure drop through the pipe.
In certain applications, different regions of the computational domain experience flow conditions that are so different that it is very difficult for a single solver to produce accurate results at the extremes. In many situations, such problems can be separated and solved using loosely coupled solvers. Each solver is chosen to provide highly accurate solutions for the prevailing flow conditions.
ESI's CFD-FASTRAN, a compressible flow solver, is ideally suited for high speed external aerodynamics problems and the multi-physics solver CFD-ACE+ is ideally suited for heat transfer problems involving conduction, convection (natural and forced) and radiation.
A large amount of aerodynamic heating is generated over hypersonic vehicles during re-entry. Thermal Protection System (TPS) materials are employed to prevent the heating from conducting into the internal cabin, which holds electronic devices, passengers and other vital components. As a time-dependent process, the material making up TPS is at a low temperature and “soaks up” the heat – the conductivity of the material transports the heat (from the vehicle surface) through the thickness. The material will also re-radiate some of the heat back to the flow – the amount depending on the emissivity of the material. A primary concern is to estimate the effects of aeroheating on the internal volume of the capsule and its effect on electronic devices, passengers and cooling systems. In this application, typically the external flow is hypersonic in nature, whereas the flow within the capsule is a very low speed flow dominated by natural convection. In addition, to hypersonic aerodynamic heating, several other physics including heat conduction, natural convection and radiation has to be accurately modeled. CFD-FASTRAN solves for the external hypersonic flow and CFD-ACE+ solves for heat conduction, convection and radiation. Exchange of heat flux/temperature data between FASTRAN and ACE occurs at defined interfaces.
The objective of this tutorial is to find the optimum bend radius R such that the pressure drop in the pipe is minimum for given a two-dimensional pipe with fixed velocity inlet.
The problem to be simulated is the inviscid, subsonic flow of air past a cylinder. The diameter of the cylinder is 1 m. The flow has a free-stream Mach number,M∞ , of 0.177. The numerical model employs only a semicylinder due to the symmetry of the flow pattern around the cylinder.
Incompressible subsonic flow past a two-dimensional backward-facing step is modeled to estimate the laminar reattachment length (i.e., the point where the separation bubble disappears on the channel floor behind the step). This is a step-by-step guided introductory tutorial for setting up a flow model in CFD-ACE+.
