The Java Virtual Wind Tunnel
A Two Dimensional Invicid Computational Fluid Dynamics
There are three examples included in this directory: a subsonic flow, a supersonic
flow, and a transonic flow. All three of these examples are based
on the Ni's Bump's problem (a simple problem that is often used to
test new flow solvers). The upper and lower edges of the grid
represent solid walls, one of which has a distinct "bump" in it. The
flow enters at the left side of the grid and exits at the right. As
the flow hits the bump, it accelerates past mach 1 and becomes
supersonic. At the rear of the bump, the flow is forced to
decelerate, so a shock wave forms just above the bump. As the
simulation reaches steady state, the shock becomes clearly visible,
particularly in the line plot of the mach number.
This transonic flow is only one of many possible flow geometries.
Although the examples all model forms of Ni's bump, the simulation
could just as well be of a wing or rocket nozzle.
Some places you can go from here:
David Y. Oh / Computational Aerospace Sciences Laboratory, MIT / firstname.lastname@example.org