Thrust and efficiency of propulsion by oscillating foils


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...
Control of flow structure on 70° swept delta wing with along-the-core blowing using numerical modeling
Küçükyılmaz, İbrahim Can; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2016)
In recent years, interest has increased in Unmanned Combat Air Vehicles (UCAVs) and Unmanned Air Vehicles (UAVs), which can be represented by simplified planforms including delta wings. Delta wings experience the formation of two counter-rotating vortices on the leeward side of the planform due to the shear layer separated from the windward side. At sufficiently high angle of attack, these vortices undergo sudden expansion, called vortex breakdown/burst, which is quite detrimental considering the aerodynami...
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...
Citation Formats
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: