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
Numerical and Experimental Analysis of Purely Pitching and Purely Plunging Airfoils in Hover
Date
2012-07-06
Author
Hızlı, Hasan
Kurtuluş, Dilek Funda
Metadata
Show full item record
Item Usage Stats
172
views
0
downloads
Cite This
Numerical and experimental study of two-dimensional purely pitching and purely plunging SD7003 and NACA0012 airfoil sections in hover mode is presented. Main objectives of the study are to provide a better understanding of the aerodynamic phenomena and the vortex topology of flapping wings for application to micro air vehicle (MAV) designs and to compare numerical and experimental results for observing the performance of the experimental setup for future applications. The commercial CFD package program Fluent 6.3 is used for the numerical simulation of the flow whereas the instantaneous velocity field data of the flow is collected by Particle Image Velocimetry (PIV) measurements. Among the current studied cases, the highest mean lift coefficient is obtained from purely plunging NACA0012 airfoil section while the lowest is obtained from purely pitching NACA0012 airfoil section. Moreover, purely plunging SD7003 airfoil section gives the lowest mean drag coefficient whereas purely pitching SD7003 airfoil section gives the highest. In a following work, a comprehensive experimental visualization will be performed with time resolved PIV (TR-PIV) measurements.
URI
https://hdl.handle.net/11511/76730
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Nonlinear Dynamic Inversion Autopilot Design for an Air Defense System with Aerodynamic and Thrust Vector Control
Bıyıklı, Rabiya; Yavrucuk, İlkay; Tekin, Raziye; Department of Aerospace Engineering (2022-2)
The study proposes complete attitude and acceleration autopilots in all three channels of a highly agile air defense missile by utilizing a subcategory of nonlinear feedback linearization methods Nonlinear Dynamic Inversion (NDI). The autopilot design includes cross-coupling effects enabling bank-to-turn (BTT) maneuvers and a rarely touched topic of control in the boost phase with hybrid control which consists of both aerodynamic fin control and thrust vector control. This piece of work suggests solut...
Numerical and experimental investigation of pitching / plunging airfoils in hover
Hızlı, Hasan; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2012)
In this thesis, results of the numerical and experimental study corresponding to four airfoils, namely SD7003, NACA0012, 10% thick elliptical, 10% thick flat plate, undergoing sinusoidal pure pitch, pure plunge and combined pitch-plunge types of hovering motion are presented. A number of cases are investigated consisting of different pitching and plunging amplitudes. The study aims to provide a better understanding of the aerodynamics phenomena and the vortex topology of flapping wings in motion for applica...
Computational fluid dynamics simulations of ship airwake
Sezer Uzol, Nilay; Sharma, A.; Long, L.N. (2005-10-01)
Computational fluid dynamics (CFD) simulations of ship airwakes are discussed in this article. CFD is used to simulate the airwakes of landing helicopter assault (LHA) and landing platform dock-17 (LPD-17) classes of ships. The focus is on capturing the massively separated flow from sharp edges of blunt bodies, while ignoring the viscous effects. A parallel, finite-volume flow solver is used with unstructured grids on full-scale ship models for the CFD calculations. Both steady-state and time-accurate resul...
Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics
Dağlı, Efe Can; Aksel, M. Haluk.; Department of Mechanical Engineering (2019)
In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method us...
Numerical analysis of radio frequency inductively coupled ion thruster and computation of its performance parameters
Bozkurt, Erdal; Alemdaroğlu, Nafiz.; Department of Aerospace Engineering (2019)
The main goal of this thesis is geometric and parametric analysis of a simulated cylin-drical two-gridded Radio Frequency Inductively Coupled (RF-ICP) ion thruster. Inaddition, instrumental performance of this thruster and the effects of a fixed shapeof the electrodes on ion trajectories are investigated. The simulations of the plasmaand the ion optics are performed by using COMSOL Multiphysics software. The firststep is checking the reliability of the software. Radial and axial simulation parametricresults...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
H. Hızlı and D. F. Kurtuluş, “Numerical and Experimental Analysis of Purely Pitching and Purely Plunging Airfoils in Hover,” 2012, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/76730.
