Coupled CFD Shape Optimization for aerodynamic profiles

The present document deals with the optimization of shape of aerodynamic profiles -- The objective is to reduce the drag coefficient on a given profile without penalising the lift coefficient -- A set of control points defining the geometry are passed and parameterized as a B-Spline curve -- These points are modified automatically by means of CFD analysis -- A given shape is defined by an user and a valid volumetric CFD domain is constructed from this planar data and a set of user-defined parameters -- The construction process involves the usage of 2D and 3D meshing algorithms that were coupled into own- code -- The volume of air surrounding the airfoil and mesh quality are also parametrically defined -- Some standard NACA profiles were used by obtaining first its control points in order to test the algorithm -- Navier-Stokes equations were solved for turbulent, steady-state ow of compressible uids using the k-epsilon model and SIMPLE algorithm -- In order to obtain data for the optimization process an utility to extract drag and lift data from the CFD simulation was added -- After a simulation is run drag and lift data are passed to the optimization process -- A gradient-based method using the steepest descent was implemented in order to define the magnitude and direction of the displacement of each control point -- The control points and other parameters defined as the design variables are iteratively modified in order to achieve an optimum -- Preliminary results on conceptual examples show a decrease in drag and a change in geometry that obeys to aerodynamic behavior principle

Numerical Simulation of Nanofluid Cooling in a Single-Cylinder Diesel Engine

Masteroppgave i energiENERGI399KMAMN-ENER

The influence of convective exchanges on coandã effect

Modeling Coandã effect has been a fundamental issue in fluid dynamic research in the XX century. It has lost some interest because of the improvement in CFD, even if it could be still important in the area of the preliminary design of aerodynamic devices that benefits of fluid deflection by convex surfaces. An effective model of Coandã effect has not been defined, and fundamental questions are still open. The influence of convective heat exchange on Coandã adhesion of a fluid stream on a convex surface in the presence of a temperature gradient between the fluid and the convex surface is a problem, which affects many practical cases, but it is still marginally approached by scientific literature. This paper aims to start an effective research direction on the effects of convective heat exchange on Coandã effect. It approaches the problem with a set of CFD simulations. It analyses the previous hypotheses, which are based on Prandtl number and evidences the need of a more effective model that accounts also for the Reynolds number

Wells turbine for wave energy conversion : a review

In the past twenty years, the use of wave energy systems has significantly increased, generally depending on the oscillating water column (OWC) concept. Wells turbine is one of the most efficient OWC technologies. This article provides an updated and a comprehensive account of the state of the art research on Wells turbine. Hence, it draws a roadmap for the contemporary challenges which may hinder future reliance on such systems in the renewable energy sector. In particular, the article is concerned with the research directions and methodologies which aim at enhancing the performance and efficiency of Wells turbine. The article also provides a thorough discussion of the use of computational fluid dynamics (CFD) for performance modeling and design optimization of Wells turbine. It is found that a numerical model using the CFD code can be employed successfully to calculate the performance characteristics of W-T as well as other experimental and analytical methods. The increase of research papers about CFD, especially in the last five years, indicates that there is a trend that considerably depends on the CFD method

Design of a low cost injection system for a small liquid fuel rocket motor

Rocket fuel injectors are in charge of propellant atomization and mixing processes, which determine the performance and stability of the liquid rocket engine itself. This small, yet significant components, are in charge of reducing the size and weight of the propellant droplets while mixing them in the shortest possible amount of time. The injector’s design and implementation must be suitable for performing their tasks in order to achieve maximum performance of the nozzle. Aiming to design and test a feasible rocket injector, a conceptual and physical design is presented, using cheap off-the-shelf stream jet nozzles, and its basic behaviour assessed. The numerical approach involves using computational fluid dynamics software (OpenFOAM) while the experimental approach involves lathe machining considerations. The numerical results indicate that the doublet injector design is feasible and mixture quality can be attained but still needs to be crafted and tested using a particular jet nozzle configuration

A semi-quantitative schlieren high-speed flow diagnostic : analysis of high-pressure-ratio, overexpanded planar flow in rocket nozzles

This work introduces a semi-quantitative schlieren (SQS) method which is used to qualitatively and quantitatively analyze complex, unsteady, compressible flows in a small, planar convergent-divergent nozzle. A basic schlieren system is used to image the evolution in time of complex supersonic flow structures, including Prandtl-Meyer expansion fans, internal shocks, near-wall oblique shocks, quasi-normal shocks, shock/boundary layer interactions, shock/shock interactions, and shock trains. The first images of shock trains in high nozzle-pressure-ratio flows are shown, and the underlying processes are described. A flow-field decomposition method is presented which allows the entire flow field to be separated into unit processes and analyzed. Various methods of analysis are presented, including a new method for the determination of node locations along a defined nozzle wall geometry using the method of characteristics. A numerical solution is developed for the analysis of a blow-down process. Computer programs which implement these solutions are presented

Experimental Study and Numerical Simulation of the Flindt Draft Tube Rotating Vortex

The dynamics of the rotating vortex taking place in the discharge ring of a Francis turbine for partial flow rate operating conditions and cavitation free conditions is studied by carrying out both experimental flow survey and numerical simulations. 2D laser Doppler velocimetry, 3D particle image velocimetry, and unsteady wall pressure measurements are performs to investigate thoroughly the velocity and pressure fields in the discharge ring and to give access to the vortex dynamics. Unsteady RANS simulation are performed and compared to the experimental results. The computing flow domain includes the rotating runner and the elbow draft tube. The mesh size of 500,000 nodes for the 17 flow passages of the runner and 420,000 nodes for the draft tube is optimized to achieve reasonable CPU time for a good representation of the studied phenomena. The comparisons between the detailed experimental flow field and the CFD solution yield to a very good validation of the modeling of the draft tube rotating vortex and, then, validate the presented approach for industrial purpose applications

Advanced Technologies in Hydropower Flow Systems

Hydropower is an essential part of the renewable energy sector. High efficiency, immediate availability, and safe operation of hydroelectric power plants are the three key issues in recent developments in the hydropower sector. This book brings together the latest achievements addressing these key factors. In addition, one contribution deals with the alternative harvesting of hydro energy from pivoted cylinders by generating flow-induced vibrations, which are unwanted phenomena in classical pump–turbine units

HPCCP/CAS Workshop Proceedings 1998

This publication is a collection of extended abstracts of presentations given at the HPCCP/CAS (High Performance Computing and Communications Program/Computational Aerosciences Project) Workshop held on August 24-26, 1998, at NASA Ames Research Center, Moffett Field, California. The objective of the Workshop was to bring together the aerospace high performance computing community, consisting of airframe and propulsion companies, independent software vendors, university researchers, and government scientists and engineers. The Workshop was sponsored by the HPCCP Office at NASA Ames Research Center. The Workshop consisted of over 40 presentations, including an overview of NASA's High Performance Computing and Communications Program and the Computational Aerosciences Project; ten sessions of papers representative of the high performance computing research conducted within the Program by the aerospace industry, academia, NASA, and other government laboratories; two panel sessions; and a special presentation by Mr. James Bailey