Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Aerodynamic analysis of flatback airfoils using vortex particle method
Download
index.pdf
Date
2014
Author
Haser, Senem Ayşe
Metadata
Show full item record
Item Usage Stats
229
views
137
downloads
Cite This
In this thesis, aerodynamic analysis of flatback airfoils, which have been proposed and investigated to improve the aerodynamic performance of thick airfoils, is studied. Vortex particle method, which is commonly used for simulation of two dimensional, incompressible, viscous flows, is used for this purpose. In the content of this thesis, vortex particle method code developed by Kaya [1] is improved by changing method of diffusion and method of vorticity releasing from solid boundary. Deterministic Particle Strength Exchange (PSE) method is implemented to solve diffusion equation. In addition, instead of vortex particle releasing algorithm, vorticity releasing algorithm, which is more suitable for PSE method, is implemented. The method and algorithm are explained in detail and results of analysis are presented. The validation and applicability of the improved code is illustrated by solving flow past a flat plate, a circular cylinder and a square cylinder. After that, flow around FB3500 series flatback airfoils at Reynolds number of 1000 are simulated by using the improved vortex particle method code. In order to compare results, laminar and unsteady Computational Fluid Dynamics (CFD) analyses are performed.
Subject Keywords
Vortex-motion.
,
Vortex flaps.
,
Aerofoils.
,
Aerodynamics.
,
Flaps (Airplanes).
URI
http://etd.lib.metu.edu.tr/upload/12618306/index.pdf
https://hdl.handle.net/11511/24298
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
AERODYNAMIC ANALYSIS OF SUPERSONIC FLOW OVER A SIMPLE AIRCRAFT GEOMETRY BY USING CST AND PANEL METHODS
Uğur, Levent; Turan, Sena; Gedik, Ramazan Kürşat; Adam, Ali Ata; Sezer Uzol, Nilay; Ertem, Sercan; Ayan, Erdem (2021-09-10)
In this paper, the aerodynamic properties of a selected aircraft geometry are calculated in supersonic flow condition using PANAIR. PANAIR is an open-source high-order panel method solver for irrotational and inviscid flows and it is more efficient than higher fidelity CFD analyses for the preliminary design process since it is faster and easier to use. A batch of supersonic analyses is completed for different wing/body configurations for the selected aircraft geometry and with various panel g...
Aerodynamic optimization of turbomachinery cascades using Euler/boundary-layer coupled genetic algorithms
Oksuz, O; Akmandor, IS; Kavsaoglu, MS (American Institute of Aeronautics and Astronautics (AIAA), 2002-05-01)
A new methodology is developed to find the optimal aerodynamic performance of a turbine cascade. A boundary-layer coupled Euler algorithm and a genetic algorithm are linked within an automated optimization loop. The multiparameter objective function is based on the blade loading. For a given inlet Mach number and baseline cascade geometry, the flow inlet and exit angles, the blade thickness and the solidity are optimized by a robust genetic algorithm. First, the Sanz subcritical turbine cascade is selected ...
FLUID-STRUCTURE INTERACTION ANALYSIS OF A FOUR-BAR FLAPPING WING MECHANISM
Beker, Can; Turgut, Ali Emre; Arıkan, Kutluk Bilge; Kurtuluş, Dilek Funda (2019-07-11)
In this paper, it is introduced to find net aerodynamic lift capacity of proposed flapping-wing micro air vehicle (FWMAV) by performing dynamical calculation and FSI (Fluid Structure Interaction) analysis of a flapping wing test system. In the flapping system, a single degree of freedom type four-bar mechanism which was used as a piezo-driven flapping wing mechanism in previous literature studies is implemented to create beating motion of the wings. For the wing structure, Calliphora Erythocephala’s wing is...
Aerodynamic Analyses of Thick Wind Turbine Airfoils for High Reynolds Numbers
ASLAN, EZGİ; Orbay Akcengiz, Ezgi; Sezer Uzol, Nilay (2021-09-08)
In this study, Computational Fluid Dynamics simulations of flow around thick have been performed. Thick airfoils are generally preferred in wind turbine blades for structural and aerodynamic performances. High Reynolds flows around thick airfoils are one of the challenging problems in wind turbine blade design due to turbulent, separated and complex flow field characteristics. In the CFD analyses, both 2-D RANS simulation approach on structured computational grids is considered. Grid sensitivity study is al...
Experimental investigation of 3D flow field around a Flapping wing making figure-of-eight motion in hover Using PIV technique
Ersöz, İrem; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2014)
This thesis presents the results of experimental investigation of vortex formation around a three dimensional flapping wing making figure-of-eight motion in hovering flight at low Reynolds numbers. These results are compared with those obtained from previous computational and experimental studies of the same flapping motions. Analysis of vortex formations around the three dimensional flapping wing and the investigations of the effect of different parameters such as the amplitude of motion in y direction and...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
S. A. Haser, “Aerodynamic analysis of flatback airfoils using vortex particle method,” M.S. - Master of Science, Middle East Technical University, 2014.