Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
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
Thrust and efficiency of propulsion by oscillating foils
Download
index.pdf
Date
2004-07-16
Author
Young, J.
Lai, J. C. S.
Kaya, Muhammed Çağrı
Tuncer, İsmail Hakkı
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
44
views
39
downloads
Cite This
Subject Keywords
Strouhal number
,
Lead edge vortex
,
Airfoil surface
,
High thrust
,
Navier stokes solver
URI
https://hdl.handle.net/11511/31771
DOI
https://doi.org/10.1007/3-540-31801-1_43
Collections
Graduate School of Natural and Applied Sciences, Conference / Seminar
Suggestions
OpenMETU
Core
Numerical and experimental analysis of tandem flapping flight
Tay, Wee Beng; Perçin, Mustafa; van Oudheusden, Bas W.; Bijl, Hester; ÇETİNER YILDIRIM, NURİYE LEMAN OKŞAN; ÜNAL, MEHMET FEVZİ (2013-06-24)
Flapping-wing Micro Aerial Vehicles (FMAVs) are equipped with a fixed tail that is primarily used for the achievement of stability and controllability of the vehicle. However, previous research has revealed that the interference between the wake of the upstream flapping wings and the tail is complex and can affect the performance of the FMAVs considerably. Hence, the current study investigates the interaction between a plunging wing and a stationary tail, in a combined experimental and numerical study. The ...
Vortex flow aerodynamics behind a symmetric airfoil at low angles of attack and Reynolds numbers
Kurtuluş, Dilek Funda (2021-11-01)
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 aerodyn...
Flow characteristics of translating flexible wings at low reynolds numbers
Yazdanpanah, Mahdi; Perçin, Mustafa; Department of Aerospace Engineering (2019)
This study experimentally investigates the flow field around surging-translating wings that are started from rest and compares the flow field characteristics with that of surging-revolving wings. Three wings with different level of chordwise flexural stiffness (i.e., highly flexible, moderately flexible and rigid) were studied. The experiments were performed in an octagonal water tank at the Reynold number of 7360 based on the terminal velocity of 0.08 m/s, and the wing chord length of 92 mm. Two-dimensiona...
Numerical investigation of thickness-to-chord ratio on aerodynamic characteristics and flow field of a low swept delta wing
Cesur, İsmail Sadi; Albayrak, Kahraman; Department of Mechanical Engineering (2019)
Recent years revealed the increased interest in Unmanned Combat Air Vehicles (UCAVs) and Unmanned Air Vehicles (UAVs) which utilize delta wing planforms, making the Delta wing studies more prominent. Delta wings are characterized by two counter-rotating vortices on leading edges formed by the detached shear layer from the windward side of the planform. Those vortical structures lower the pressures on the suction side of the wing therefore contributes to the increase of the lifting and maneuvering capacity o...
Beam switching reflectarray with rf mems technology
Bayraktar, Ömer; Aydın Çivi, Hatice Özlem; Department of Electrical and Electronics Engineering (2007)
In this thesis 10x10 reconfigurable reflectarray is designed at 26.5 GHz where the change in the progressive phase shift between elements is obtained with RF MEMS switches in the transmission lines of unit elements composed of aperture coupled microstrip patch antenna (ACMPA). The reflectarray is illuminated by a horn antenna, and the reflected beam is designed to switch between broadside and 40° by considering the position of the horn antenna with respect to the reflectarray. In the design, the transmissio...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
J. Young, J. C. S. Lai, M. Ç. Kaya, and İ. H. Tuncer, “Thrust and efficiency of propulsion by oscillating foils,” 2004, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/31771.