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.

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.

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.

This unsteady simulation involves a moving body and demonstrates the use of chimera and 6-DOF modeling features in CFD-FASTRAN. The flow has a free stream Mach number of 0.5. The freestream temperature and pressure are 101325 Pa and 288.16K, respectively.

This unsteady simulation involves a moving body and demonstrates the useof chimera and 6-DOF modeling features in CFD-FASTRAN. 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 mixing is important in a wide variety of applications. One such application is high speed air breathing aircraft engines (supersonic combustion/hypersonic aircrafts). As aircrafts continue to fly at higher speeds, complete mixing has to be achieved within shorter combustion chambers to minimize fuel consumption,  avoid combustion instabilities and decrease emissions. The turbulent mixing of two streams of gases (propane and air) is modeled in this tutorial.

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.

In this tutorial, a pitching airfoil is modeled. The airfoil oscillates in a sinusoidal fashion in the freestream. Two grid systems are employed namely, the airfoil and the background grid system. A prescribed motion model is employed to create the airfoil grid motion in the stationary background grid. The moving airfoil grid and the stationary background grid communicate using chimera methodology. The solution is carried out in two steps. First a steady state solution is obtained with stationary airfoil. Next, the moving grid simulation is carried out using the steady state solution as initial condition.

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.

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.

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.