The Java Virtual Wind Tunnel

A Two Dimensional Invicid Computational Fluid Dynamics Simulation

Version 1.0Beta1


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 / bamf@attbi.com