A Conceptual Design of I-125 Generator at the HANARO

2009 ◽  
Author(s):  
Heonil Kim ◽  
Jonghark Park ◽  
Byungchul Lee ◽  
Heetaek Chae ◽  
Youngki Kim
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Conceptual Design ◽  
Neutron Capture ◽  
Research Reactor ◽  
Thermal Hydraulics ◽  
Neutron Physics

A simple I-125 generating device at the research reactor, HANARO, is developed. Xenon-124 gas circulates continuously in the generator producing I-125 by neutron capture and the I-125 is adsorbed at the upper part of the generator, which is to be chemically recovered in a hot-cell. The continuous xenon circulation technology is devised by the design of the generator structure with the consideration of thermal hydraulics and neutron physics involved. A computational fluid dynamics technique is used for the conceptual design of the generator.

CONCEPTUAL DESIGN AND STUDY OF FLOW THROUGH A DUAL BELL NOZZLE AT DIFFERENT ALTITUDES USING COMPUTATIONAL FLUID DYNAMICS

2021 ◽  
Vol 11 (3) ◽  
pp. 38
Author(s):  
SAI RAJA CHADA JITHENDRA ◽  
DEEPAK AKELLA SRI RAM ◽  
SRINIVAS BASWANTH PAPPULA SASHENDRA ◽  
NATHIPAM GANESH ◽  
◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Conceptual Design ◽  
Flow Through ◽  
Dual Bell ◽  
Different Altitudes

scholarly journals Conceptual Design of an Unmanned Fixed-Wing Aerial Vehicle Based on Alternative Energy

2019 ◽  
Vol 2019 ◽  
pp. 1-13 ◽  
Author(s):  
Alan G. Escobar-Ruiz ◽  
Omar Lopez-Botello ◽  
Luis Reyes-Osorio ◽  
Patricia Zambrano-Robledo ◽  
Luis Amezquita-Brooks ◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Solar Cells ◽  
Conceptual Design ◽  
Alternative Energy ◽  
Dynamics Analysis ◽  
Preliminary Design ◽  
Aerodynamic Analysis ◽  
Computational Fluid Dynamics Analysis ◽  
Aerial Vehicle

This paper focuses on the aerodynamics and design of an unmanned aerial vehicle (UAV) based on solar cells as a main power source. The procedure includes three phases: the conceptual design, preliminary design, and a computational fluid dynamics analysis of the vehicle. One of the main disadvantages of an electric UAV is the flight time; in this sense, the challenge is to create an aerodynamic design that can increase the endurance of the UAV. In this research, the flight mission starts with the attempt of the vehicle design to get at the maximum altitude; then, the UAV starts to glide and battery charge recovery is achieved due to the solar cells. A conceptual design is used, and the aerodynamic analysis is focused on a UAV as a gliding vehicle, with the calculations starting with the estimation of weight and aerodynamics and finishing this stage with the best glide angle. In fact, the aerodynamic analysis is obtained for a preliminary design; this step involves the wing, fuselage, and empennage of the UAV. In order to achieve the preliminary design, an estimation of aerodynamic coefficients, along with computational fluid dynamics analysis, is performed.

Conceptual design and analysis of hybrid airships with renewable energy

2017 ◽  
Vol 232 (11) ◽  
pp. 2144-2159 ◽  
Author(s):  
Lanchuan Zhang ◽  
Mingyun Lv ◽  
Junhui Meng ◽  
Huafei Du
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Renewable Energy ◽  
Conceptual Design ◽  
Aerodynamic Characteristics ◽  
Wing Loading ◽  
Design Point ◽  
Independent Variable ◽  
Solar Powered ◽  
Dynamics Method

An increasing focus on hybrid airships and the developments in renewable energies has allowed a methodology for conceptual design and analysis to be described. After a model presented and its aerodynamic characteristics obtained through a computational fluid dynamics method, two types of hybrid airships, solar powered at high altitudes and hydrogen powered for cargo, are demonstrated using a wing loading as their independent variable. Then the constraints determining the design point are presented. Parametric estimates of two types for component mass are then illustrated on distribution diagrams. And the sensitivity of wing loading and its effects on hybrid airships are discussed.

Reduced Aerodynamic Drag for Truck-Trailer Configurations Using Parametrized CFD Studies

2012 ◽  
Author(s):  
Srdan Pavlović ◽  
Magnus Andersson ◽  
Jonas Lantz ◽  
Matts Karlsson
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Drag Reduction ◽  
Conceptual Design ◽  
Fuel Economy ◽  
Aerodynamic Drag ◽  
Foreseeable Future ◽  
Heavy Duty ◽  
Computational Fluid Dynamics Cfd

In the presented work, two studies using Computational Fluid Dynamics (CFD) have been conducted on a generic truck-like model with and without a trailer unit at a speed of 80 km/h. The purpose is to evaluate drag reduction possibilities using externally fitted devices. A first study deals with a flap placed at the back of a rigid truck and inclined at seven different angles with two lengths. Results show that it is possible to decrease drag by 4%. In a second study, the flap has been fitted on the tractor and trailer units of a truck-trailer combination. Four settings were surveyed for this investigation, one of which proved to decrease drag by up to 15%. A last configuration where the gap between the units has been closed has also been evaluated. This configuration offers a 15% decrease in drag. Adding a flap to the closed gap configuration decreases drag by 18%. New means of reducing aerodynamic drag of heavy-duty (HD) vehicles will be important in the foreseeable future in order to improve the fuel economy. The possibilities of reducing drag are prevalent using conceptual design.

Conceptual design methodology of a box wing aircraft: A novel commercial airliner

2018 ◽  
Vol 232 (14) ◽  
pp. 2651-2662 ◽  
Author(s):  
Pavlos Kaparos ◽  
Charalampos Papadopoulos ◽  
Kyros Yakinthos
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Aspect Ratio ◽  
Conceptual Design ◽  
Design Methodology ◽  
Aerodynamic Performance ◽  
Design Parameters ◽  
Sweep Angle ◽  
Continuous Surface ◽  
Wing Tips

In this work, the development of a conceptual design methodology of an innovative aircraft configuration, known as box wing, is presented. A box wing aircraft is based on a continuous-surface nonplanar wing formation with no wing-tips. The A320 medium range conventional cantilever wing aircraft is used as both the reference aircraft and the main competitor of the box wing aircraft. Based on the A320 characteristics and dimensions, a complete aerodynamic analysis of the box wing configuration is made by means of layout design and computational fluid dynamics studies, highlighting the aerodynamic and operating advantages of the box wing configuration compared to the A320 aircraft. The aspect ratio and the Oswald factor of a box wing aircraft differ significantly from the corresponding ones of A320 and provide increased aerodynamic performance. The increased aerodynamic performance leads by consequence, to lower fuel consumption, thus allowing longer range for the same payload or greater payload for the same range, contributing to the efforts for greener environment. In this work, the design methodology begins by estimating the critical initial design parameters, such as aspect ratio, dihedral angle, sweep angle, and taper ratio, which are continuously refined via an iterative process based on a conceptual design study. Various flying scenarios are studied using computational fluid dynamics and analytical calculations, in order to compare the performance of the box wing and the conventional A320, having always the same mission and payload conditions. The conceptual results show that the novel box wing configuration has considerable aerodynamic performance advantages compared to the conventional A320 aircraft.

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