This unsteady simulation involves a moving body and demonstrates the
useof chimera and 6-DOF modeling features in CFD-FASTRAN. This tutorial will be setup to run in Parallel. The flow has
a free stream Mach number of 2.0 at AOA of 5 deg. The free-stream
temperature and pressure are 101325Pa and 288.16K, respectively. The
simulation includes two separate 6DOF motion models. 6DOF model # 1
governs the motion of the second stage (payload vehicle), and 6DOFmodel
# 2 governs the motion of the first stage (booster vehicle). The
payload vehicle has a rocket nozzle that is modeled with a time
dependent inlet condition simulating rocket ignition. First a
steady-state solution of the combined vehicle flying at 5 deg. angle of
attack is obtained. Then at time t=0, the rocket motor ignites and
pressure builds up between the stages resulting in the separation of
the two vehicles. The thrust integration option is employed to account
for the thrust component at the nozzle chamber.
Turbulent subsonic flow of air past a cylinder is modeled. Diameter of the cylinder is 1m. The flow has a free-stream Mach number,M, of 0.5.The free stream temperature and pressure are 300K and 1 x 105 Pa, respectively.The Reynolds number, Re, of the flow, based on the chord length of the airfoil, is 9 x 106.The computational domain is modeled with Chimera technology using an O-mesh around the cylinder which is overset on a Cartesian background mesh.
The turbulent flow past a NACA 0012
airfoil is modeled. The flow has a free-stream Mach
number,M, of 0.55 at an angle of attack of 8.34 degrees. The Reynolds number, Re, of the
flow, based on the chord length of the airfoil, is 9x 106.
The problem to be simulated is the turbulent flow past a NACA-0012
airfoil. The flow has a free-stream Mach number, M, of 0.55 at an
angle of attack, alpha, of 8.34 degrees. The Reynolds number, Re, of the flow,
based on the chord length of the airfoil, is 9x106. For this case,
the flowfield develops a supersonic bubble near the leading edge of the airfoil
upper surface. Furthermore, the flow is slightly separated at the foot of the shock that terminates the supersonic region. For this
problem, the k-epsilon turbulence model is employed.
The flow path inside a sprinkler is studied in this tutorial. Turbulence is accounted for by using
the K-Epsilon model to accurately predict the flowfield.
The problem to be simulated is inviscid, supersonic flow of air past a blunt body. The numerical model employs only one half of the body due to the symmetry of the flow pattern. The flow has a free-stream Mach number, M∞, of 23.5. Due to high free stream Mach number, the flow develops high temperatures which initiates chemical reactions between the various components of air. These reactions include 1) dissociation of diatomic Oxygen 2) dissociation of diatomic Nitrogen, 3) dissociation of nitrous Oxide 4) reaction of diatomic Nitrogen with oxygen and 5) reaction of Nitrous Oxide with Oxygen.
The problem to be simulated is supersonic flow over a ramp
in a channel. A 3-D grid is employed for the problem; however, the flow is
essentially 2D in nature. The flow is characterized by an oblique shock
generated due to the change in the direction of the supersonic flow caused by
the wedge. The flow has a free-stream Mach Number M of 2.0. The free stream
temperature and pressure are 300K and 101,300Pa, respectively.
This tutorial investigates the etching of an Aluminum surface due to
Chlorine gas when a mixture of Argon (Ar) and Chlorine (Cl2) flows over
an Aluminum substrate. Similiar reactors are used in semiconductor fabrication and MEMS applications.
In order to assign various BCs on one single geometry, it has to be split into multiple geometries. The same is the case for surface sources. More face groups will affect reading and saving time later on in CFD-GUI and CFD-VIEW. Therefore, it might be neccessary to combine the geometries that have same BCs into a single geometry at a later stage. This tutorial describes the steps for reorganizing the geometry.
