High speed wind tunnels are widely used in the study of fluid flow behavior around various objects. The air flow in the starting step of supersonic wind tunnels is transient including strong shock waves caused by the interaction of the tunnel main stream and the boundary layer at walls. To arrive in running step, the tunnel must be designed so as these waves leave immediately the test section. ...

high speed wind tunnels are widely used in the study of fluid flow behavior around various objects. the air flow in the starting step of supersonic wind tunnels is transient including strong shock waves caused by the interaction of the tunnel main stream and the boundary layer at walls. to arrive in running step, the tunnel must be designed so as these waves leave immediately the test section. ...

The air intake should be operated at design conditions to achieve a high total pressure recovery and optimum mass capture ratio. current research focuses on the numerical simulation of supersonic hypersonic inlet its starting unstarting characteristics. 2D RANS equation for has been solved using k-oSST turbulence model. in-house code algorithm based have also validated in due process used subse...

─ Supersonic flows associated with missiles, aircraft, missile engine intake and rocket nozzles are often steady. The shape of the nozzle geometry is increasingly attractive in heating, ventilation and air conditioning applications. The objective of the present work is to simulate and understand Supersonic flows with twin free jet Flow at various Mach numbers. The purpose is to precisely unders...

Intake design for supersonic engines, in common with other engineering design problems, is application dependent and the true challenges are in meeting performance targets over the required Mach and Reynolds number ranges while complying with the multitude of constraints imposed by the aircraft/missile and its mission. The fundamentals and limitations of efficient ram compression are well under...

Numerical study of two dimensional supersonic hydrogen-air mixing layer is performed to investigate the effect of turbulence and chemical additive on ignition distance. Chemical reaction is treated using detail kinetics. Advection upstream splitting method is used to calculate the fluxes and one equation turbulence model is chosen here to simulate the considered problem. Hydrogen peroxide is us...

the aim of this study was to evaluate the effect of evaporative media as gas turbine intake air cooling method on pressure drop of cartridge air filters. this study performed under the laboratory condition, using stainless steel test rig with specified dimensions to investigate the role of evaporative media in air cooling as well as its effects on new and used cartridge filters (as representati...