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
Vortex flow aerodynamics behind a symmetric airfoil at low angles of attack and Reynolds numbers
Download
17568293211055653.pdf
Date
2021-11-01
Author
Kurtuluş, Dilek Funda
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
319
views
404
downloads
Cite This
The low Reynolds number aerodynamics is important to investigate for micro air vehicle applications. The current paper covers numerical simulations to present the downstream development of the wake patterns and detailed analysis of the vortices generated at the downstream of NACA 0012 airfoil around the critical angle of attack where the instantaneous vortex patterns are oscillatory and differ from the mean vortex pattern for low Reynolds numbers ranging from 1000 to 4000. The instantaneous and mean aerodynamic forces, pressure and skin friction coefficients, and vorticity values are compared in addition to the path of the vortex centers, their longitudinal and lateral spacings, Karman spacing ratios, and distortion ratios at the wake of the airfoil in regard to the different Reynolds numbers investigated. The streamwise and crosswise velocities of the vortex cores and relative velocities at different transverse locations are also discussed and presented in detail. The correlations between different non-dimensional numbers (St, Re, Ro) are obtained at these low Reynolds numbers investigated.
Subject Keywords
Unsteady aerodynamics
,
low Reynolds number
,
airfoil wake
,
Karman spacing ratio
,
NACA 0012 AIRFOIL
,
STABILITY
URI
https://hdl.handle.net/11511/94942
Journal
INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES
DOI
https://doi.org/10.1177/17568293211055653
Collections
Department of Aerospace Engineering, Article
Suggestions
OpenMETU
Core
Aerodynamic parameter estimation of a supersonic missile with rapid speed variation by using kalman filtering
Bayoğlu, Tuğba; Kutay, Ali Türker; Department of Aerospace Engineering (2016)
This study aims to develop an approach for the aerodynamic parameter estimation problem for supersonic air to air missile with rapid speed variation, as well as large variation of aerodynamic parameters with respect to Mach number. In literature, most of the estimation techniques require that estimator is time independent. Therefore, most of the aerodynamic parameter estimation methods are applied for air vehicles which have control over their speed or which can operate at relatively constant Mach number so...
Experimental design and statistical modeling for efficient wind tunnel testing
Savaş, Özgün; Kutay, Ali Türker; Department of Aerospace Engineering (2019)
Wind tunnel testing is an essential procedure to measure the aerodynamic forces and moments on an air vehicle. In this thesis, a method is presented to perform such test in an efficient way. First, an experimental design process is carried out before the testing in order to cover the flight regime as fine as possible with the least possible number of tests. After the determination of the test matrix and conducting the wind-on tests, the modeling of the output data is the next step. On that matter, since the...
Aerodynamic parameter estimation using flight test data
Kutluay, Ümit; Platin, Bülent Emre; Mahmutyazıcıoğlu, Gökmen; Department of Mechanical Engineering (2011)
This doctoral study aims to develop a methodology for use in determining aerodynamic models and parameters from actual flight test data for different types of autonomous flight vehicles. The stepwise regression method and equation error method are utilized for the aerodynamic model identification and parameter estimation. A closed loop aerodynamic parameter estimation approach is also applied in this study which can be used to fine tune the model parameters. Genetic algorithm is used as the optimization ker...
Error analysis and assessment of unsteady forces acting on a flapping wing micro air vehicle: free flight versus wind-tunnel experimental methods
Caetano, J. V.; Perçin, Mustafa; van Oudheusden, B. W.; Remes, B.; de Wagter, C.; de Croon, G. C. H. E.; de Visser, C. C. (IOP Publishing, 2015-10-01)
An accurate knowledge of the unsteady aerodynamic forces acting on a bio-inspired, flapping-wing micro air vehicle (FWMAV) is crucial in the design development and optimization cycle. Two different types of experimental approaches are often used: determination of forces from position data obtained from external optical tracking during free flight, or direct measurements of forces by attaching the FWMAV to a force transducer in a wind-tunnel. This study compares the quality of the forces obtained from both m...
Steady-State CFD Analysis of 3D Bio-inspired Flapping Wing Models
Bektaş, Mürvet; Kurtuluş, Dilek Funda; Güler, Mehmet Ali (2018-07-11)
The aerodynamics of insects flying at low Reynolds numbers is considered for Micro Air Vehicles (MAV) designs. The aim of this study is to analyze different flapping wing models and to predict generated forces and vortices around the wings. The analyses are significant for understanding properties of flying animals like birds, insects and for improving MAVs more. For three insect species (namely, bumblebee, hawkmoth, and hummingbird), three dimensional (3D) wing models are numerically analyzed at different ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
D. F. Kurtuluş, “Vortex flow aerodynamics behind a symmetric airfoil at low angles of attack and Reynolds numbers,”
INTERNATIONAL JOURNAL OF MICRO AIR VEHICLES
, vol. 13, pp. 0–0, 2021, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/94942.