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.
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.
1. Unsteady expansion.
2. Circular Cylinder.
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.
The Visual Wind Tunnel DSMC demonstration program is restricted to the number of
simulated molecules that permit real-time animation of the moving molecules to
illustrate selected two-dimensional and axially symmetric flows at the molecular
level. This version employs about 16,000 simulated molecules at (800x600) resolution.