A plane subsonic jet was subjected to periodic oscillations in the near nozzle region by a twin vane system. During excitation, the jet was found to spread significantly and entrain mass much more than its steady counterpart. Time averaged static pressure measured in the flow field with a disc probe exhibited prominent well defined suction regions different from that of a steady jet.

We establish the existence and stability of multidimensional steady transonic flows with transonic shocks through an infinite nozzle of arbitrary cross-sections, including a slowly varying de Laval nozzle. The transonic flow is governed by the inviscid potential flow equation with supersonic upstream flow at the entrance, uniform subsonic downstream flow at the exit at infinity, and the slip bo...

We consider the spectral stability of certain traveling wave solutions for the Boussinesq ‘abc’ system. More precisely, we consider the explicit sech(x) like solutions of the form (φ(x − wt), ψ(x − wt) = (φ, const.φ), exhibited by M. Chen, [7], [8] and we provide a complete rigorous characterization of the spectral stability in all cases for which a = c < 0, b > 0.

The aim of this experimental study is two-dimensional investigation of cargo behavior after separation which is carried out in the subsonic wind tunnel. Given that the real separation occurs in three-dimension, the results of this study may be widely used in numerical aerodynamic studies for verification of new computational methods and they can be used as the reference results in this area. So...

Accidental release scenarios such as flammable gas leaks or ruptures of pipes and pressurised process-equipment normally originate high velocity jets which, if ignited, give rise to jet fires. Although the direct effects of jet fires are considered to be relatively smaller than that associated to other types of fires, they are characterized by high heat fluxes and, especially if there is flame ...

We show that for steady compressible potential flow in a class of straight divergent nozzles with arbitrary cross-section, if the flow is supersonic and spherically symmetric at the entry, and the given pressure (velocity) is appropriately large (small) and also spherically symmetric at the exit, then there exists uniquely one transonic shock in the nozzle. In addition, the shock-front and the ...