Design Aspect of Wind Turbine Blade:
INTRODUCTION:
In this assignment you will use ANSYS FLUENTto investigate the aerodynamics of an airfoil. The study is to be carried out on an accurate dimensional model of a standard NACA-2415 airfoil:
In PART1 ofthe assignment you are asked to carry out an analysis ofthe airfoil at a angle of attack of 10 degrees speed and inlet Mach number of 0.4066 and 0.8. The chord length is 1 m. In PART2, you are asked to modifythe model to change angle of attack (from O to 12 degrees with step 2 degrees). In PART3, you are asked to report on yourwork. to guantify and discuss yourfindings and to provide a critical appraisal of your modelling methodology.
Asolid model ile and mesh file airfoil-naca2415.mshcan be found in the Coursework/NACA-2415 Airfoil folder on Study Space.
All files in the folder should be copied to your own file sgace before beginning any work.
PART 1:Initial Analysis:
Using the standard methodology described in the Basic Modelling of External FlowTutorial as a guide, importthe supplied model into ANSYS Fluent, set up the CFD model, solve it using ANSYS Fluent and examine the characteristics ofthe flow. For EOE the initial analysis, the model should be set up identically to the model investigated during the tutorial sessions exceptthat the choice ofthe inlet Mach number and angle of attack. In carrying outthe modelling you should:
Create the flow domain geometry and isolate the fluid region.
Identify and label the flow domain boundaries.
Set up the controlling parameters for surface and volume meshing.
Model the boundary layer using layer inflation.
Generate Preview
Groups showing the mesh on key surfaces.
Generating the volume mesh.
Set up the physics ofthe flow and assign appropriate boundary conditions.
Set up the initial flow conditions and the solution monitors and controls.
Solve the model and monitor the solution convergence.
Create Contour and Streamline plots.
Assess the quality ofthe boundary layer modelling from the y+ distribution.
Use the Fluent Function Calculatorto determine lift and drag forces.
On completion ofthe analysis you should summarise yourfindings, and illustrate the general flow field around the airfoil highlighting any problem areas or interesting flow features using combinations of appropriate Contour and Streamline plots. These plots should be produced IN COLOUR. No more than ten images should be provided and each image should be annotated and discussed to indicate the features you found to be of interest. Provide a clear statement of the results of your investigations into the effect of flow domain size and select suitable flow domain dimensions for PART2.
PART 2:
AERODYNAMIC MODIFICATIONS
Carry out research into ways of improving the aerodynamics of airfoil.
Initially, you should consultthe basic
reference materials provided in the
Module Information / CFD ASSIGNMENT /References folder on Study Space. Based on your researches, choose two features you believe will improve the aerodynamic performance ofthe airfoil and describe why you believe that they will be effective.
In addition modify the given airfoil model (angle of attack), and repeat the analysis of PART1 for your modified model. As before, illustrate the flow field around the modified model using combinations of appropriate Contour and Streamline plots. All plots should be produced IN COLOUR. No more than ten images should be provided and again, each one should be annotated to indicate the features you to be of interest and to highlight any flow imfprov ements you observe. Plot dependence of drag and lift coefficient on angle of attack.