Here we utilize a non-Fourier approach to model buoyancy aiding or opposing flow of Maxwell fluid in the region of stagnation-point towards a vertical stretchable surface. Flow field is permeated by uniform transverse magnetic field.

Shell181Two different heating processes namely i prescribed surface temperature PST and ii constant wall temperature CWT are analyzed. Through suitable transformations, the similarity equations are formed which are treated numerically for a broad range of magnetic interaction parameter. The obtained solutions are compared with available articles under limiting situations and such comparisons appear convincing.

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The structure of boundary layer depends on a parameter measuring the ratio of free stream velocity to the stretching sheet velocity. The momentum transport via stretching boundary is opposed by both fluid relaxation time and magnetic interaction parameter. Thermal boundary layer expands as the effects of transverse magnetic field and thermal relaxation time are amplified.

A reduction in heat penetration depth is anticipated for increasing values of thermal relaxation time. The variation in wall slope of temperature with increasing thermal relaxation time appears similar at any assigned value of Prandtl number. A comparative study of aiding and opposition flow situations is presented and deliberated. Abstract Here we utilize a non-Fourier approach to model buoyancy aiding or opposing flow of Maxwell fluid in the region of stagnation-point towards a vertical stretchable surface.

Grant support.This article addresses the nonlinear radiation effect on two-dimensional oblique stagnation point flow in a porous medium. Constitutive equations of viscoelastic fluid are employed in the mathematical development of the relevant problem. A comparative study of present results with that of previous studies have been made in a limiting sense and shown through tabular values. Excellent agreement is noted which clearly shows that the used numerical scheme is stable and the results are highly accurate.

Impact of sundry variables in the flow quantities of interest are discussed. Thermal boundary layer thickness can be controlled due to small value of radiation parameter and surface heating parameter.

It is also noted that with the increase in value of porosity parameter Kthe velocity increases but the momentum boundary layer thickness decreases in the region of stagnation point. Moreover, the streamlines are plotted to predict the flow pattern. This is a preview of subscription content, log in to check access. Rent this article via DeepDyve. Heat Transf.

Asaithambi, A. Google Scholar. Attia, H. Tamkang J. Bataller, R. Heat Mass Transf. Bejan, A. Springer, New York Chen, C. Cheng, J. Porous Media 61 Chiam, T. Cortell, R. Dorrepaal, J. Fluid Mech.

Drazin, P.

Ebay account restricted associated with another accountElbashbeshy, E. Garg, V. Hossain, M. Husain, I. Ingham, D. Elsevier, Oxford Ishak, A. Javed, T. Asia Pac. Keller, H. Two dimensional laminar flows.

Khan, M. Porous Media 7123—37 We present an experimental and computational investigation of time-varying flow in an idealized fully occluded 45 degrees distal end-to-side anastomosis. Two geometric configurations are assessed, one where the centerlines of host and bypass vessels lie within a plane, and one where the bypass vessel is deformed out of the plane of symmetry, respectively, termed planar and non-planar. In the planar geometry the stagnation point follows a straight-line path along the host artery bed with a path length of 0.

By contrast in the non-planar case the stagnation point oscillates about a center that is located off the symmetry plane intersection with the host artery bed wall, and follows a parabolic path with a 0.

A definition of the oscillatory shear index OSI is introduced that varies between 0 and 0. In both models, regions of elevated oscillatory shear were spatially associated with regions of separated or oscillating stagnation point flow. These changes in the dynamic behavior of the stagnation point and the oscillatory shear distribution introduced by out-of-plane graft curvature may influence the localization of vessel wall sites exposed to physiologically unfavorable flow conditions.

Abstract We present an experimental and computational investigation of time-varying flow in an idealized fully occluded 45 degrees distal end-to-side anastomosis.To browse Academia. Skip to main content. Log In Sign Up.

**The Aerodynamics of Flight**

Comparative study of stagnation point anomalies by means of shock capturing and shock fitting unstructured codes. Aldo Bonfiglioli. Renato Paciorri. Two differ- ent approaches have been used to simulate the strong de- Figure 1.

Schematic of the mis-alignment problem en- tached bow shock: shock-capturing on anisotropically re- countered with triangular elements when simulating a fined meshes and shock-fitting.

Concerning the boundary shock wave or a boundary layer flow. When looking at wall quantities such as pressure, skin friction and heat transfer these appear to be elements triangles and tetrahedra greatly simplify auto- more heavily affected by the boundary layer mesh than by matic grid generation and feature-based adaptation.

In this paper we try to establish to which extent shock and boundary-layer resolution contribute to the observed stagnation point anomalies. This is schematically shown in Fig. To date, however, the accuracy delivered by unstructured grid codes in hyper- The chosen testcase had originally been proposed by the sonic applications is markedly inferior to that exhibited NASA Langley aerothermodynamic team in the frame- by their structured-grid counterpart.

These cylinder. Beside the reference results obtained using deficiencies manifest themselves among others as over- the NASA codes LAURA structured-grid and FUN2D predicted heat rates and anomalous recirculation bubbles unstructured-gridthe only other references known to in the surrounding of the stagnation point.

It consists in the two-dimensional, hypersonic, laminar flow past the forebody of circular cylinder.

Ender 5 3d printer ukFreestream conditions for the hypersonic 2D 2. In the present study, shock modeling has been accom- present study have been derived from a structured quadri- plished by means of two different approaches: shock- lateral grid consisting in 64 CVs in the wall normal di- capturing on anisotropically refined meshes and shock fit- rection and 60 CVs along the semi-circular forebody sur- ting. In both cases the gasdynamic is solver is EulFS [9], face. These include the capability to ting schemes for the spatial discretization and implicit align the outer inflow boundary with the captured bow pseudo time-stepping to accelerate convergence towards shock and also to optimize the distribution of grid points steady state.

When the bow shock is captured, a finite in the boundary layer region. Starting from the LAURA number of grid levels are generated by repeated applica- mesh, three sequences of grids have been obtained by cut- tion of the anisotropic mesh refinement AMR algorithm ting each quadrilateral cell into two triangles using three described in [10] and implemented in the freely available different triangulation patterns which we shall refer to in software ANGENER [11].

When the bow shock is fit- the following as triangulation patterns of type 1, 3 and 6. In the triangular grid provided by the Lan- domain. The motion of the shock front and the state val- gley benchmark, also shown in Fig. Since the mesh puted according to the Rankine-Hugoniot equations. Due covers the whole forebody of the cylinder, the Langley to the displacement of the shock wave, the mesh in the triangular grid, which we have labeled type 1, is not sym- neighbourhood of the shock front needs to be regener- metric with respect to the direction of the freestream flow, ated at each time-step to guarantee that the shock points see Fig.

This was deliberately done so as to empha- and edges are part of a constrained Delaunay triangula- size grid induced anisotropies in the computed solution. In the present For each of these three types of triangulation patterns, work, the shock-fitting grids have been built upon the un- the subsequent grid levels share with the level 0 grids adapted level 0 grids used in shock-capturing mode and the same meshpoint location and cell connectivity of the therefore differ from these only in the neighbourhood of 40 layers of cells closest to the walls.

This was done the shock front. Figure 2 should illustrate well the differ- following the choice made in [8].

## Buoyancy effects in stagnation-point flow of Maxwell fluid utilizing non-Fourier heat flux approach

Outside of this near- ences between the anisotropically adapted mesh and the wall layer of cells, which encloses the boundary layer, shock-fitting one: the fitted shock is shown by means a the computational domain has been re-meshed using the solid black line and overlayed upon the anisotropically anisotropic mesh refinement algorithm AMR descibed adapted mesh. Further details concerning the shock- in [10].The ascending optimized trajectory to minimize the heat load in the hypersonic part is used to perform the study.

The study includes the cooling for the stagnation point, the leading edges for wings and engine, and other parts of the aerospace plane that are close to the leading edges. The laminar case for the stagnation point and both laminar and turbulent cases for the leading-edge heating have been considered. The amount of heat rate total, radiative, and convective and the mass of liquid coolant needed for cooling are calculated.

A design of minimum inlet-outlet areas for the amount of liquid needed for cooling is made with the consideration of the coolant's physical constraints in liquids and gaseous states. The comparison shows that the hydrogen is a clear winner as a candidate for coolant and it saves mass as compared to all other five coolants. The study shows that there are no fundamental barriers for the cooling system of the vehicle in terms of its coolant mass and area size for coolant passage, especially if H-2 is used.

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Powered by:.Skip to main content. Volume 25, Issue 2. No Access. Tools Add to favorites Download citation Track citations. Previous article. Adolfo Martucci. Experimental characterization of the hypersonic flow around a cuboid. Ross S. Michael R. Microroughness-induced disturbances in supersonic blunt body flow.

Evaluation of blunt body velocity gradient at the shock tube end-wall. Constraint-based parameterization using FFD and multi-objective design optimization of a hypersonic vehicle. Fluid-thermal modeling of hypersonic vehicles via a gas-kinetic BGK scheme-based integrated algorithm. Ultra-high temperature ceramics developments for hypersonic applications.

Thomas K.

Kof 2012 mod apkA two-way coupled Euler-Lagrange method for simulating multiphase flows with discontinuous Galerkin schemes on arbitrary curved elements. Brian R. Connor C. Daniele E. Rowland T. Experimental study of forward-facing cavity with energy deposition in hypersonic flow conditions.

Insulating and absorbing heat of transpiration in a combinational opposing jet and platelet transpiration blunt body for hypersonic vehicle.

## The influence of out-of-plane geometry on pulsatile flow within a distal end-to-side anastomosis

Megan E. Christopher M. Aerothermodynamic Design Optimization of Hypersonic Vehicles. Commissioning of the T6 Stalker Tunnel. Peter L. Rate Effects in Hypersonic Flows. An aerothermodynamic design optimization framework for hypersonic vehicles. High temperature and thermal non-equilibrium effects on the determination of free-stream flow properties in hypersonic wind tunnels.

Aerodynamic heating of inflatable aeroshell in orbital reentry. Heat flux characteristics within and outside a forward facing cavity in a hypersonic flow. Aerothermodynamic effects of controlled heat release within the hypersonic shock layer around a large angle blunt cone.The forthright intention of the present investigation is to analyze the up-to-date progress in Jeffrey nanofluid flow past an electromagnetic sheet by utilizing the properties of nonlinear convection, radiation, convective boundary condition, zero mass flux condition and Arrhenius activation energy.

The flow equations are transformed by applying appropriate transformations into a pair of self-similarity equations. Further similarity equivalences are numerically solved through Runge—Kutta-based shooting method. Graphs and tables are structured to analyze the behavior of sundry influential variables. The results acquired showed good agreement with the previous notable works. Through this study we observed that improvement in Lorentz force in the positive x -direction strengthens the momentum, which intensifies the transfer of heat energy from the boundary, resulting in reduced fluid temperature.

This is a preview of subscription content, log in to check access. Rent this article via DeepDyve. MamathaUpadhya, S. Powder Technol. Raju, C. Saleem, S. Santhosh, H. Zaib, A.

Msmdownloadtool oneplus 7 proHeat Fluid Flow 29 5— Rashid, M. Buongiorno, J. ASME J. Heat Transf. Narahari, M. Heat Fluid Flow 27 123—47 Reddy, J.

Alexandria Eng. Khan, M. Sultan, F. Pramana 92 221 Irfan, M. Solids— Kumar, R. Hayat, T. Thermal Anal.

Rashid, S. Dhlamini, M. Design Eng. Ram, R. Umar, M.

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