ESI Group CFD Portal - Simulation of Missile Aerodynamics using Parallel Computing

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.

Details

This tutorial covers the following subjects:

Setting a model name and title for the problem.
Reading a multi domain, DTF grid, and building a CFD-FASTRAN model.
Setting fluid properties such as molecular weight.
Setting initial values for the flow field to perform a steady state simulation.
Setting initial values for the flow field to perform unsteady simulation.
Setting appropriate boundary conditions.
Setting up a Chimera problem with overset grids.
Setting up a moving grid simulation by associating the 6-DOF models with the grids.
Setting up time dependent pressure and temperature boundary conditions.
Setting up thrust model.
Setting solution iterations and cycles.
Choosing a suitable time-integration scheme and setting CFL numbers.
Setting up a model for running CFD-FASTRAN solver in parallel mode.

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