Yutük, Kaan
Modern fighter aircraft compulsorily demand high maneuverability capability, which is mainly provided by an improved aerodynamic performance at high angles of attack. This is achieved by mostly employing strakes and canards. In this study, adjoint-based configuration and leading edge shape optimizations of a strake on a double-delta wing configuration are performed. SU2 is employed for flow and adjoint solutions. SU2 flow solutions are first verified on solutions for adaptive grids. In the configuration optimization, the sweep angle of the strake is considered as design variable. In the leading edge shape optimization, the free-form deformation box is employed. Remarkably, it is only allowed to modify the leading edge without changing the flat strake surface. Optimization studies are performed for both inviscid and turbulent flows at 10° and 22.5° angles of attack, respectively. It is shown that the sweep angle optimization based on turbulent flow solutions improves the L/D ratio by about 8.4% at 10° angle of attack and 2.7% at 22.5° angle of attack. In addition, the leading edge shape optimization based on turbulent flow solutions improves the L/D ratio by about 4.5% at 10° angle of attack and 3% at 22.5° angle of attack.


Aeroelastic Modelling and Testing of a Thin Laminated Composite Missile Fin/Wing
Aslan, Göktuğ; Kırımlıoğlu, Serdar; Kurtuluş, Dilek Funda (null; 2017-06-09)
Missile fins or wings exposed to different coupled aerodynamic loads during the mission or flight at subsonic and supersonic velocity profile. Aerodynamic loads varying with the angle of attack and the velocity profile may cause some structural fatigue and failure problems. In order to achieve such problems, high strength materials such as composites are required. In this work, a laminated composite missile fin was investigated in terms of the strength varying with the aerodynamic profile. The fiber orienta...
Generic trim analysis and simulation algorithm creation for design and optimization of the fixed wing aircraft
Özdemir, Mustafa; Kurtuluş, Dilek Funda (2021-09-10)
In order to design a fixed wing aircraft, certain phases are needed to perform. From these phases, trim analysis and simulation are very crucial for design process. Trim and simulation analysis enable to calculate performance and stability characteristics of the aircraft. After aerodynamic, weight and engine database creation, the next step is trim analysis and simulations. However, database creation phase requires a huge amount of computing time, and for the preliminary design phase it is needed to perform...
Hovering Control of a Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20)
In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of t...
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 ...
Turbulent flow and acoustic predictions over open cavity configurations at transonic speeds
Çoşkun, Seyfettin.; Özyörük, Yusuf; Department of Aerospace Engineering (2019)
In modern military fighters, internal carriage of weapons is vital in terms of high survivability, low observability and aerodynamic performance of the fighter. During store release phases of operation, the aircraft will have to fly with the cavity exposed to free stream conditions. When an aircraft internal weapons bay is exposed to free stream of air, a highly unsteady and complex flow field develops within the cavity. This triggers intense aero-acoustic environment in and around the cavity. Highly complex, un...
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