DSMC

Direct Simulation Monte-Carlo

The DSMC (Direct Molecular Simulation - Monte Carlo Method) gas flow simulation technique was pioneered by Emeritus Professor Graeme Bird at the Department of Aeronautical Engineering, University of Sydney. The method was originally used for simulation of rarefied gas flow around rentry vehicles, but has now progressed to the stage of being a useful tool for solving a large range of aerodynamic and aerospace problems.

How does the method work?
Where can you get the software?
View some sample solutions.

Some of the projects now being undertaken in the school using this method are

  • Simulation of flow separation in near continuum region.
  • Rankine-Heugonot weak/strong shock reflection solutions.
  • Nano-Fluid Simulations.
  • Investigation of stability of low Reynold's number flows.
    •

    Here are some flow pictures of our recent projects.
     
    Interaction of Shock and Boundary Layer Flow

    Mach No. Contours

    Rankin-Heugonot Mach Reflection Flow

    Density Contours for Mach Reflection Solution


    Nano-size Cavity Flow (Moving Lid)

    Flow Direction Vectors (Not including Amplitude) for Flow induced in a Moving Lid Cavity.


    Gas Jet Instability.

    Mach Number and Vertical Velocity Contours showing asymetric solution for gas jet at Reynolds number 250.
    Initial jet is symmetric parabolic flow from nozzle.



    Time varying solutions have been obtained which match the unsteady nature of this type of flow.


    Transonic near-continuum flow.

    Mach Number Contours showing transonic shock solution for NACA0012 at an angle of attack of 1.76 degree. A simulated Reynolds number of infinity is employed.


    for further information contact doug.auld@sydney.edu.au.
     

     Links to DSMC Pages