In the frame of the project "Gasdynamically initiated nanoparticle production", detailed numerical and experimental investigations of pseudo-shock systems in a Laval nozzle with parallel side walls have been carried out. The location of the pseudo-shock system is defined in this system of two chocked Laval nozzles by the ratio of the critical cross sections A2*/A1*, the stagnation pressure loss across the shock system and viscous losses. The wall pressure distributions and high velocity Schlieren videos recorded in the experiments are compared to the results of a steady and an unsteady numerical simulation. Corresponding results have been found
Three-dimensional numerical investigations on the nozzle start-up side load physics were performed. ...
An X type pseudo-shock wave oscillation in a supersonic diffuser is experimentally investigated by f...
This paper is devoted to the experimental study of a circular converging nozzle in under-expanded co...
The scope of this work is to investigate the structure and stochastic asymmetry of pseudo-shock syst...
A detailed experimental investigation of the influence of small gaps on a pseudo-shock system has be...
A pseudo-shock system in a rectangular nozzle with parallel side walls is investigated at different ...
The flow in a Supersonic Injection Feeder involves relatively thick boundary layers in a narrow chan...
The computations of a non-reacting nozzle-flow problem and a reacting impinging jet problem using a ...
A Laval nozzle with its typical convergent and then divergent shape has the interesting thermodynami...
It is well known that when a shock-boundary layer interaction is comparatively strong, the shock in ...
In the high-speed flow in duct, the shock wave which has occured when the supersonic flow was decela...
Scramjet operation in the lower hypersonic regime between Mach 4 and 7 is characterized by what is c...
This thesis presents an experimental study of droplet acceleration in a shock-driven two-phase flow....
In this paper, the Pseudo shock structure in a convergent–long divergent duct is investigated using ...
Supersonic air jets from the D'Laval nozzle of designed Mach number 2.0 were experimentally investig...
Three-dimensional numerical investigations on the nozzle start-up side load physics were performed. ...
An X type pseudo-shock wave oscillation in a supersonic diffuser is experimentally investigated by f...
This paper is devoted to the experimental study of a circular converging nozzle in under-expanded co...
The scope of this work is to investigate the structure and stochastic asymmetry of pseudo-shock syst...
A detailed experimental investigation of the influence of small gaps on a pseudo-shock system has be...
A pseudo-shock system in a rectangular nozzle with parallel side walls is investigated at different ...
The flow in a Supersonic Injection Feeder involves relatively thick boundary layers in a narrow chan...
The computations of a non-reacting nozzle-flow problem and a reacting impinging jet problem using a ...
A Laval nozzle with its typical convergent and then divergent shape has the interesting thermodynami...
It is well known that when a shock-boundary layer interaction is comparatively strong, the shock in ...
In the high-speed flow in duct, the shock wave which has occured when the supersonic flow was decela...
Scramjet operation in the lower hypersonic regime between Mach 4 and 7 is characterized by what is c...
This thesis presents an experimental study of droplet acceleration in a shock-driven two-phase flow....
In this paper, the Pseudo shock structure in a convergent–long divergent duct is investigated using ...
Supersonic air jets from the D'Laval nozzle of designed Mach number 2.0 were experimentally investig...
Three-dimensional numerical investigations on the nozzle start-up side load physics were performed. ...
An X type pseudo-shock wave oscillation in a supersonic diffuser is experimentally investigated by f...
This paper is devoted to the experimental study of a circular converging nozzle in under-expanded co...