Stagnation Region Radiative Ablation of Asteroidal Meteoroids in the Rosseland Approximation

2014 ◽  
Vol 28 (4) ◽  
pp. 598-607 ◽  
Author(s):  
Chul Park
Keyword(s):  
Stagnation Region ◽  
Rosseland Approximation

Measurement of surface flow features at the stagnation region of a swept cylinder

1994 ◽  
Author(s):  
S. Mangalam ◽  
S. Venkateswaran ◽  
S. Korategere
Keyword(s):  
Surface Flow ◽  
Stagnation Region ◽  
Flow Features

EQUILIBRIUM AND PERFECT GAS AIR BEHAVIOR IN THE STAGNATION REGION

2018 ◽  
Author(s):  
Paulo Toro ◽  
Guilherme Icaro Andrade de Oliveira ◽  
Lucas Carvalho ◽  
Luísa Mirelle Santos ◽  
Raul Farias ◽  
...  
Keyword(s):  
Perfect Gas ◽  
Stagnation Region

scholarly journals Flow towards a Stagnation Region of a Vertical Plate in a Hybrid Nanofluid: Assisting and Opposing Flows

Mathematics ◽  
2021 ◽  
Vol 9 (4) ◽  
pp. 448
Author(s):  
Iskandar Waini ◽  
Anuar Ishak ◽  
Ioan Pop
Keyword(s):  
Radiation Effects ◽  
Vertical Plate ◽  
Similarity Transformation ◽  
Fluid Motion ◽  
Hybrid Nanoparticles ◽  
Problem Solver ◽  
Hybrid Nanofluid ◽  
Al2o3 Nanoparticles ◽  
Nanofluid Flow ◽  
Stagnation Region

This study investigates a hybrid nanofluid flow towards a stagnation region of a vertical plate with radiation effects. The hybrid nanofluid consists of copper (Cu) and alumina (Al2O3) nanoparticles which are added into water to form Cu-Al2O3/water nanofluid. The stagnation point flow describes the fluid motion in the stagnation region of a solid surface. In this study, both buoyancy assisting and opposing flows are considered. The similarity equations are obtained using a similarity transformation and numerical results are obtained via the boundary value problem solver (bvp4c) in MATLAB software. Findings discovered that dual solutions exist for both opposing and assisting flows. The heat transfer rate is intensified with the thermal radiation (49.63%) and the hybrid nanoparticles (32.37%).

Effect of radiative heat loss on steady hypersonic flow past a blunt body

1967 ◽  
Vol 29 (3) ◽  
pp. 485-494 ◽  
Author(s):  
M. I. G. Bloor
Keyword(s):  
Numerical Solution ◽  
Heat Loss ◽  
Blunt Body ◽  
Radiative Heat ◽  
Constant Density ◽  
Axially Symmetric ◽  
Radiative Heat Loss ◽  
Stagnation Region ◽  
Expansion Procedure ◽  
Axis Of Symmetry

Using the grey gas approximation, the effect of radiative heat loss on axially symmetric flows is studied. Using an expansion procedure about the axis of symmetry, a numerical solution for the stagnation region is found taking the shock to be spherical. The results of this calculation are compared with the results of Lighthill's non-radiative constant density solution.

Integrated Combustor and Vane Concept in Gas Turbines

2010 ◽  
Author(s):  
Budimir Rosic ◽  
John D. Denton ◽  
John H. Horlock ◽  
Sumiu Uchida
Keyword(s):  
Gas Turbines ◽  
Integrated System ◽  
Axial Distance ◽  
Stagnation Region ◽  
Manufacturing Costs ◽  
Fully Integrated ◽  
Wetted Area ◽  
Novel Concept ◽  
Industrial Gas Turbine ◽  
Cooling Air

This paper numerically investigates the interaction between multiple can combustors and the first vane in an industrial gas turbine with 16 can combustors and 32 vanes in order to find ways of reducing the overall cooling requirements. Two promising concepts for the overall cooling reduction are presented. In the first, by minimising the axial distance between the combustor wall and the vane, the stagnation region at the LE of every second vane can be effectively shielded from the hot mainstream gases. The LE shielding allows continuous cooling slots to be used (as an alternative to discrete cooling holes) to cool downstream parts of the vane using a portion of the saved LE showerhead cooling air. The second concept proposes a full combustor and first vane integration. In this novel concept the number of vanes is halved and the combustor walls are used to assist the flow turning. All remaining vanes are fully integrated into the combustor walls. In this way the total wetted area of the integrated system is reduced, and by shielding the LEs of the remaining vanes the total amount of cooling air can be reduced. The proposed combustor and first vane integration does not detrimentally affect the aerodynamics of the combustor and vane system. The concept also simplifies the design and should lower the manufacturing costs.

Radiation Effect on the Mixed Convection Flow of a Viscoelastic Fluid Along an Inclined Stretching Sheet

2012 ◽  
Vol 67 (3-4) ◽  
pp. 195-202 ◽  
Author(s):  
Muhammad Qasim ◽  
Tasawar Hayat ◽  
Saleem Obaidat
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Viscoelastic Fluid ◽  
Radiative Heat ◽  
Heat Transfer Analysis ◽  
Convection Flow ◽  
Viscoelastic Parameter ◽  
Homotopy Analysis ◽  
Rosseland Approximation ◽  
Momentum Boundary Layer

This study concentrates on the heat transfer analysis of the steady flow of viscoelastic fluid along an inclined stretching surface. Analysis has been carried out in the presence of thermal radiation and the Rosseland approximation is used to describe the radiative heat flux in the energy equation. The equations of continuity, momentum and energy are reduced into the system of governing differential equations and solved by homotopy analysis method (HAM). The velocity and temperature are illustrated through graphs. Exact and homotopy solutions are compared in a limiting sense. It is noticed that viscoelastic parameter decreases the velocity and boundary layer thickness. It is also observed that increasing values of viscoelastic parameter reduces the thickness of momentum boundary layer and increase the heat transfer rate. However, it is found that increasing the radiation parameter has the effect of decreasing the local Nusselt number

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