CFD Simulation Videos 

More coming soon... 


Detonation Processes in a Variable Crosssection Chamber  2006 
The detonation processes occuring in a variable crosssection combustion chamber have been simulated for a hydrogenair reacting flow. The chamber consists of a large diameter tube and two small identical tubes connected on each side through frustums. The channel is closed to the left and open to the right. A 2D, timeaccurate, finitevolumebased method is used for the computations. Two cases are simulated, corresponding to initiation from the open and closed ends. Click here for a more detailed research paper. 
Ignition from the Left (Closed) 
Ignition from the Right (Open) 


Standing Detonation Wave Types 3 and 3'  2006 
When the incoming Mach number is high enough, a standing detonation wave can be initiated after multiple shock reflections in the wedge or afterbody area (Type 3) or directly at the wedge tip fromt the bow shock (Type 3'). If standing in the aftbody area, the wave is normal with interference by the shock or expansion before it. If it is standing in the wedge area, the wave is oblique. See the PDW Type 1 and 1' introduction for the computational parameters. For the Type 3 case, the Mach number is 5 and the wedge angle is 5 degrees. For the Type 3' case, the Mach number is 6 and the wedge angle is 15 degrees. Click here for a more detailed research paper. 
Type 3 SDW Pressure Contours 
Type 3 SDW Closeup Pressure Contours 
Type 3' SDW Pressure Contours 


No Detonation Mode Type 2  2006 
For a small wedge angle, a steady shock system can form ove the wedge with no induced combustion. The simulation results show that the final thermodynamic parameters of the flow behind the last shock are lower than the CJ state. See the PDW Type 1 and 1' introduction for the computational parameters. Click here for a more detailed research paper. 
Type 2 PSW Pressure Contours 


Propagating Detonation Wave Types 1 and 1'  2006 
A propagating detonation wave can be initiated after multiple shock reflections in the wedge or afterbody area. The Type 1 video shows the pressure contours created from this type of detonation wave. The upstream Mach number is 3, the wedge angle is 5 degrees and the reactive flow is a uniform mixture of hydrogen and oxygen. In the Type 1' model, detonation is induced from a bow shock at the tip of the wedge. For that simulation, the Mach number is 5 and the wedge angle is 15 degrees. Timedependent, 2D Euler equations of an inviscid, nonheatconducting, reacting gas flow were used. A finite volume algorithm was used with up to 25x150 cells, a 10e7 second time step, a twotemperature nonequilibrium model and a RogersChinitz two step hydrogen/oxygen reaction with five species. Click here for a more detailed research paper. 
Type 1' PDW Pressure Contours 
Type 1 PDW Pressure Contours 


Mach Reflection Induced Detonation  2004 
Below, two videos are shown of the pressure and temperature changes after detonation of a hydrogenair mixture by Mach reflection waves over a 2D wedge. 
Pressure Animation 
Temperature Animation 