A dominant mode of transmission for the respiratory disease COVID-19 is via airborne virus-carrying aerosols. As national lockdowns are lifted and people begin to travel once again, an assessment risk associated with different forms public transportation required. This paper assesses in context a ride-sharing motorbike taxi—a popular choice paratransit South South-East Asia Sub-Saharan Africa. Fluid dynamics plays significant role understanding fate droplets ejected from susceptible...

In the present study, dynamics of blood flow in saccular cerebral aneurysms is investigated. The aneurysm considered to be located at an arterial bend human vascular system. field analyzed computationally by three-dimensional Navier-Stokes equation for laminar incompressible Newtonian fluid. Circular and elliptical necks different sizes are studied. wall rigid simplicity. Hemodynamic parameters such as velocity, pressure, vortices, shear stress so on characterization field. Results showed...

Shock wave-boundary layer interactions (SWBLI) are observed in several practical high-speed internal flows, such as compressor blades, turbine cascades, nozzles and so on. induced oscillations (SIO), aerodynamic instabilities so-called buffet flutter, aeroacoustic noise vibration the detrimental consequences of this unsteady shock-boundary interactions. In present study, a numerical computation has been performed to investigate compressible flow characteristics around 12% thick biconvex...

Pulsatile flow in an axisymmetric rigid-walled model of abdominal aortic aneurysm (AAA) has been analyzed numerically for various dilations considering blood as a Newtonian fluid and Non-Newtonian respectively. Physiologically realistic waveform which include Reynolds number between 97 to 407 is used pulsatile inlet. A finite volume method solve the governing equation two dimensional, unsteady, laminar incompressible fluid. Comparisons with previously published work on basis special case...

Present investigation deals with the interaction of an incident oblique shock wave on a turbulent boundary layer over wavy surface. The was generated by 8 deg wedge in freestream Mach number 2.0. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) equations k–ω shear stress transport (SST) turbulence model were used for numerical computation. computed results are good agreement experimental measurement and direct simulation (DNS) data case plain flat plate. To identify effect...

Transonic flow over a supercritical airfoil leads to the appearances of unsteady shock waves in theflow field. At certain conditions, interaction with boundary layer becomescomplex and generates self-excited oscillation, lift fluctuation thus initiate buffet. In presentstudy, Reynolds averaged Navier-Stokes equations k-? SST turbulence model has been applied predictthe induced buffet onset for NASA SC(2) 0714. The free streamtransonic Mach number is kept range 0.71 0.75 while angle attack...

Three-dimensional numerical simulations are performed to study the migration dynamics of a deformable bubble that is spherical at an initial time near corner formed by two vertical walls. Near-wall this rising studied investigating its path, wake, shape and velocity. A finite volume approach coupled with VOF (volume-of-fluid) method adopted solve incompressible Navier–Stokes equation track gas–liquid interface. From study, it found inertia dictated bubble–walls interaction as progressively...

Nozzles are generally designed to produce thrust in a direction perpendicular its exit plane. In high speed flight vehicles, rapid control of (i.e. vectoring) is an obvious requirement for performance aerospace applications. Shock vector one the efficient ways achieve this vectoring. present study, bypass mass injection used generate shock vectoring planar supersonic Converging-Diverging (CD) nozzle. Injection was done by 10mm×10mm square channel which kept at diverging section Investigation...

Article Control of Transonic Flow with Non-Equilibrium Condensation around a Circular Arc Blade using Pump was published on March 1, 2009 in the journal International Journal Turbo & Jet-Engines (volume 26, issue 1).

The single expansion ramp nozzle (SERN) is severely overexpanded when the vehicle at low speed, which hinders its ability to provide optimal configurations for combined cycle engines. over-expansion leads flow separation as a result of shock wave/boundary-layer interaction (SWBLI). Flow separation, and presence shocks themselves, in performance loss SERN, leading reduced thrust increased pressure losses. This study investigates effectiveness wall cooling enhancing an SERN by controlling...

For modern supersonic vehicles, thrust vector control is a conspicuous prerequisite to accomplish high performance aerospace applications. Thrust chiefly falls into few classifications, for example, mechanical and shock control. Shock outstanding amongst other approaches achieve this A bypass mass injection used generate vectoring in planar Convergent-Divergent (CD) propulsion nozzle study 10×10 square mm channel was the injection. This kept perpendicular at diverging section of studied...

The cause and development of many cardiovascular diseases are related to the nature blood flow mechanical behaviour vessel. Moreover, plaque (stenosis) rapture can be occurred as a result interaction between plaque, leading clot formation stroke. In present study, with was numerically modelled. A pulsatile used mimic real through artery. rheological properties considered Newtonian well non-Newtonian. Fibrous cap thickness varied from 0.1 mm 2.0 mm. Many vortex rings appeared at pre-...

A numerical analysis of physiological blood flow in a rigid artery has been performed to observe the variation pattern and hemodynamic parameters under influence double stenoses. finite volume method employed solve governing equations for two dimensional, unsteady, laminar an incompressible Newtonian fluid. The dynamics feature have studied by wall pressure, streamline contour, shear stress axial velocity distribution all models. Besides, time average pressure studied. interspacing distance...

Abstract In this paper, the geometry of a supersonic inlet isolator is modified by introduction two-dimensional (2D) bump to control complex lip shock wave/boundary layer interaction (SWBLI). The general shape whose profile designed primarily based on inviscid theory oblique waves, which accommodates effect freestream conditions; particularly, flow Mach number. Further, geometric constraints are taken into consideration generate contoured bump. This well-designed generic tested in range...

Transonic flow over an airfoil involves shock induced oscillation at certain free steam Mach number and angle of attack due to the interaction wave with boundary layer which consequences fluctuating lift drag coefficient, aero acoustic noise vibration, high cycle fatigue failure (HCF), buffeting so on. In present study, Reynolds Averaged Navier-Stokes (RANS) equations have been used predict transonic buffer corresponding aerodynamics behaviour NASA SC(2) 0714 supercritical airfoil. RANS...

The unsteady phenomena in the transonic flow around airfoils are observed field of fan, compressor blades and butterfly valves, this causes often serious problems such as aeroacoustic noise vibration. In or supersonic where vapor is contained main flow, rapid expansion may give rise to a non-equilibrium condensation. present study, effect condensation moist air on shock induced oscillation plate was investigated numerically. results showed that case with condensation, aerodynamic...

Transonic flow around a symmetric disc butterfly valve is associated with the appearance of shock waves on surfaces. In this case, interaction between and boundary layers becomes complex thus generates flow-induced aerodynamic instability. transonic or supersonic where vapour contained in main flow, rapid expansion may give rise to non-equilibrium condensation. present study, effect condensation moist air shock-induced field oscillation was investigated numerically. The results showed that...

From the time of its invention, Gurney flap has been successfully employed as high lift augmentation device to enhance aerodynamic performance modern aircraft wings. These small flaps are located perpendicularly at suction side an airfoil near trailing edge. By addition gurney wake is stabilized which ensures laminar flow over and thus shifts shock. This study investigated effect a on NACA 2412 for subsonic condition. Flap height ranges from 2% 5% chord length. The investigation was...