Supersonic jet flow facility is a remarkable special experimental facility. It could model the true atmosphere condition. The supersonic jet flow field was calculated by solving full N-S equation to decide the suitable model dimension.
In order to study the properties of the output and high frequency rotation of pneumatic generator, we designed a supersonic jet installation for the pneumatic generator experiment.
Some nonuniform initial sata By calcultions of the transonic nozzle fowifield of several sample motors and using their results as input data for jet calcultion, the factors relative to drag ereated by the jet tab and the supersonic jet impingement on the jet tab calculated to obtain the drag.
The flowfields of an underexpanded jet counter to a supersonic stream containing multi shock (e.g. bow shock and Mach disk), contact discontinuities and shear layers are very complicated.
The interaction of supersonic jets with external acoustic waves is investigated in connection with the emission of sound of discrete frequency by the jets.
A plausible physical scheme explaining the appearance and maintenance of the oscillations of supersonic jets with discrete frequency was proposed in [1].
As far as is known to the authors, the results obtained for three-dimensional problems for the interaction of supersonic jets with each other or with barriers are primarily experimental (for example, [1-6]).
Here we give an approximate analytic solution of the problem of a supersonic jet discharging into a medium at rest or into a supersonic co-flowing stream.
A flow pattern created by the interaction of a supersonic flow with a transverse sonic or supersonic jet injected normally to the direction of the main flow through a circular aperture in a plate is considered.