Numerical Study the Effect of Blade Number on Archimedes Screw Turbine Utilized in Pico-Hydro in Horizontal Position

Application of Archimedes Screw Turbine (AST) on pico-hydro has been very popular due to its capability to has a high torque with small flow rate and environmentally friendly to biotic of vicinity. This study uses CFD to investigate AST performance when the number of blades is varied. Independency of mesh is conducted to find an efficient number of mesh and it is obtained at 80 thousand mesh. Variation A, B and C respectively has 4,6, and 9 blades varied to analyze the correspondence with torque, pressure loss and velocity contour. The results show that with a higher number of blades would make higher torque. This is because energy extraction from water would be more efficient at higher number blade. However, the side back at such number would arise such as the higher-pressure loss. This is corresponding to energy balance where a high delta pressure is proportional with a generated energy turbine.

Comparison of Aerodynamic Characteristics of NACA 0012 and NACA 2412 Airfoil

A comparison between NACA 0012 and NACA 2412 has been made by comparing the lift co- efficient, drag co-efficient, pressure contour and velocity contour at various angles of attack. The process has been done taking steady state flow around NACA-0012 and NACA-2412 airfoil using 1m chord length and a velocity of 88.65m/s. The main aim is to understand the aerodynamic characteristics of both the airfoils at different angles of attack and draw a conclusion on which performs better under the same conditions. Modelling and numerical analysis has been carried out by using commercially available CFD software, which is a convenient method of analysis since computational methods are more preferred to experimental methods due to low expenses involved. The numerical results demonstrated are compatible with those of the theory. This confirms the validity of using Computational Fluid Dynamics (CFD) as a reliable alternative to experimental procedures.

Numerical investigation of conveyor wing shape type effect on ocean waste collection behavior

In this paper, an attempt has been made to assess how effective waste-collecting uses the conveyor wing. This wing-equipped conveyor will later be installed in front of the ship. In this work, a simulation model is a conveyor and wing without the ship. A numerical investigation based on Reynolds Averaged Navier Stokes (RANS) for predicting the flow pattern characteristics, velocity contour, and resistance. The focus of the present study is the impact of wing shape on waste collection in calm water through the application of numerical methods. The three variations of wing shape used are solid wing shape, square hollow wing shape, and circle hollow wing shape. It is done using speed variations of 1 to 12 knots. From the analysis of velocity contour, circle hollow wing is faster in collecting waste, then followed by hollow square wing and solid wing. From the flow pattern analysis, the circle hollow wing model is easier to make ocean waste come closer to the winged conveyor than the square wing and solid wing model. It is known that winged conveyors can only be used to collect ocean waste at low speeds. Then based on resistance comparison, it is also known that the resistance of winged conveyors from the largest to the smallest is the solid wing, hollow circle wing, and hollow square wing, respectively.

Aerodynamic Analysis of a Popular Automobile Model with Various Add-On Devices using Computational Fluid Dynamics

This project involves analyzing the aerodynamic parameters of the vehicle and proposing the necessary changes in design to obtain better fuel economy and speed. The original, popular model was modified by the addition of spoilers, front splitters, vortex generators, diffusers, side skirts and front air dams. The popular model and the modified model are compared with respect to velocity contour, velocity streamline contour, velocity vector. It has been found that for the modified model the drag co-efficient can be reduced by 34 % and the downward force can be reduced by 19 %.

SIMULASI NUMERIK PADA SILINDER DENGAN SUSUNAN SELANG-SELING (STAGGERED) DALAM SALURAN SEGI EMPAT MENGUNAKAN K Ԑ MODEL

Abstrak— Silinder digunakan pada alat penukar kalor untuk meningkatkan luasan perpindahan panas antara permukaan utama dengan fluida di sekitarnya. Idealnya, material untuk membuat silinder harus memiliki konduktivitas termal yang tinggi untuk meminimalkan perbedaan temperatur antara permukaan utama dengan permukaan yang diperluas. Aplikasi silinder sering dijumpai pada system pendinginan ruangan, peralatan elektronik, motor bakar, trailing edge sudu turbin gas, alat penukar kalor, dengan udara sebagai media perpindahan panasnya. Ada berbagai tipe silinder pada alat penukar kalor yang telah digunakan, mulai dari bentuk yang relatif sederhana seperti silinder segiempat, silindris, anular, tirus atau pin sampai dengan kombinasi dari berbagai geometri yang berbeda dengan jarak yang teratur dalam susunan segaris (in-line) ataupun selang-seling (staggered). Dalam penelitian ini bertujuan untuk mengetahui karakteristik boundary layer turbulen pada Cylinder tersusun staggered untuk kasus dengan cara mendapatkan data secara kualitatif dan kuantitatif pada a) Coefficient of Pressure (Cp) , Nusselt Number dan (c) Velocity contour . Parameter tersebut diukur pada daerah mid span dengan, . Penelitian ini menggunakan software Fluent 6.3.26 dimana pada penelitian secara numerik digunakan turbulence model yaitu k realisable dengan discretization Second Order Upwind mengunakan software Fluent . Analisa pada penelitian numerik dilakukan secara 2 dimensi (2D) Unsteady Reynolds Averages Navier Stokes. Didapat bahwa dengan meningkatkan Re maka hal yang terjadi Cd pada silinder mengalami penurunan apabila aliran tersebut diganggu oleh silinder yang lain pada susunan staggered karena akibat kenaikan turbulensi aliran, turbuensi aliran meningkat juga mengakibatkan meningkatnya perpindahan panas ditandai dengan kenaikan Nu.

COMPARISON OF AERODYNAMICS CHARACTERISTICS OF NACA 0015 & NACA 4415 AEROFOIL BLADE

NACA 0015 and NACA 4415 aerofoil are most common four digits and broadly used aerodynamic shape. Both of the shapes are extensively used for various kind of applications including turbine blade, aircraft wing and so on. NACA 0015 is symmetrical and NACA 4415 is unsymmetrical in shape. Consequently, they have big one-of-a-kind in aerodynamic traits at the side of widespread differences of their utility and performance. Both of them undergo the same fluid principle while applied in any fluid medium giving dissimilar outcomes in aerodynamics behavior. On this work, experimental and numerical investigation of each NACA 0015 and NACA 4415 is done to decide their performance. For this purpose, aerofoil section is tested for a prevalence range attack of angle (AOA). The study addresses the performance of NACA 0015 and NACA 4415 and evaluates the dynamics of flow separation, lift, drag, pressure and velocity contour and so on.

Comparison of Aerodynamics Characteristics of NACA 0015 & NACA 4415

NACA 0015 and NACA 4415 aerofoil are most common four digits and broadly used aerodynamic shape. Both of the shapes are extensively used for various kind of applications including turbine blade, aircraft wing and so on. NACA 0015 is symmetrical and NACA 4415 is unsymmetrical in shape. Consequently, they have big one-of-a-kind in aerodynamic traits at the side of widespread differences of their utility and performance. Both of them undergo the same fluid principle while applied in any fluid medium giving dissimilar outcomes in aerodynamics behavior. On this work, experimental and numerical investigation of each NACA 0015 and NACA 4415 is done to decide their performance. For this purpose, aerofoil section is tested for a prevalence range attack of angle (AOA). The study addresses the performance of NACA 0015 and NACA 4415 and evaluates the dynamics of flow separation, lift, drag, pressure and velocity contour and so on. This additionally enables to layout new optimistic aerofoil, which is critical to enhance the efficiency and performance of an aircraft in terms of lift enhancement and drag reduction.

Impact on the Performance of Micro-Nozzle Straight Exit Section

The FLUENT6.3 software is applied to simulate the supersonic flow in micro convergent-divergent nozzle. The simulation is complemented by computing steady 2-D Navier-stokes equations to analyze the pressure contour and velocity contour inside the micro nozzle which has straight exit section or not and the length of straight exit section l. Also the performances of fluent mass coefficients and thrust force efficiencies are studied. The numerical results show: That the nozzle has straight exit section or not and the section length l affect the pressure contour and velocity contour inside the thruster. Compared to the nozzle that has no straight exit section, the minimum pressure region and the maximum velocity region are close to the center of exit in the nozzle that has straight exit section. Also the affected region is increased. When the throat Reynolds number Re is small, the flow coefficient Cd and thrust coefficient ηF firstly increase then decrease with the increase of l.