The optimal pressure differential for a desired net forward flow rate of a Tesla-type valve is evaluated and demonstrated in this tutorial. Simulation Manager allows the automation of a parametric / optimization study by controlling all analysis tools from one central application. It executes a simulation recipe that contains all the steps as a Python script. This tutorial will introduce the user to Python scripts and to use them to control CFD-GEOM parameters and CFD-ACE+ solver.

The optimization template feature of SimManager is used to find the maximum lift/drag ratio of a NACA 0012 airfoil by varying the angle-of-attack The goal of this modeling effort is to find the angle-of-attack (design variable) of the airfoil at which the maximum value of the lift/drag ratio (cost function) occurs for a given altitude and free-stream Mach number.

Discussion of model setup in CFD-GUI is given, including the use of the
parametric input feature for setting angle-of-attack and user defined
output subroutine for determining lift/drag ratio from the solution
results. The SimManager optimization template is setup to read the cost
function (lift/drag ratio) from the output file of the user defined
output subroutine and vary the CFD-ACE(U) parameter which
controls angle-of-attack. SimManager controls the simulation process by
running solver jobs and automatically varying the angle-of-attack of
the airfoil for each run until a local maximum value of the lift/drag
ratio is reached. SimManager plots the lift/drag ratio versus angle of
attack, and the lift/drag
ratio versus optimizer iteration as output.

Simulation Manager allows the automation of a parametric / optimization study by controlling all analysis tools from one central application. It executes a simulation recipe that contains all the steps as a Python script. This tutorial will introduce the user to Python scripts and to use them to control CFD-GEOM parameters and CFD-ACE+ solver. The effect of pressure differential on the forward/reverse flow rates of a Tesla-type valve is demonstrated in this tutorial.

In this tutorial, an automated parametric study of heat conduction between concentric cylinders is presented. The steady state conductive heat transfer to the air-gap between
infinitely long concentric thick-walled cylinders is modeled for various airgap lengths. Based on a table of input values, Simulation Manager calls CFD-GEOM to update model geometry and grid, changes boundary conditions, then runs the CFD-ACE+ solver for each case.

An automated study of the effect of geomteric and flow parameters on the laminar flow past a backward facing step is demonstrated in this tutorial. The step height, channel height and the inlet flow velocity are varied. The automation is achieved by controlling all analysis tools from one central application: Simulation Manager. It executes a simulation recipe that contains all the steps as a Python script. This tutorial will introduce the user to predefined simulation templates available in Simulation Manager. However, users can define their own scripts to modify geometry, gridding, volume conditions (VC), boundary conditions (BC), create custom GUI, conduct parametric and optimization studies.

The purpose of this tutorial is to show how to setup and post-process a
parametric study
involving geometric parameters. The example used for this tutorial is
the case of a finned heat
exchanger in which the fin thickness will be varied. The goal is to
determine the fin thickness that result in the lowest temperature on the
model.

This tutorial also shows how CFD-CADalyzer can be interfaced with CAD
packages such as Autodesk Inventor, IronCAD, SolidEdge, SolidWorks, or
ProE.

An
automated parametric study of oil flow through a compliant orifice is presented
in this tutorial. Based
on a table of input values, Simulation Manager calls CFD-GEOM to update model
geometry and grid, then runs the CFD-ACE+ solver for each case. The radius R of
the compliant orifice is varied.

Model dependencies can be used to simulate complex rigid body motions. In this example, a pitching airfoil with flap is used to demonstrate this feature.