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.

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.

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 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.