Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft

Aircraft design processes need to ensure that the aircraft will be aeroelastically stable within its operational envelope. This paper presents an overview of the static aeroelastic analysis results, flutter analysis and gust response analysis results of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), the aerodynamic theory employed by Nastran for subsonic flows. DLM requires all lifting surfaces to be parallel to the free stream. In this study, aerodynamic load distribution is corrected by including the camber and the angle of incidence of the wing through the addition of initial downwash to the aerodynamic mesh. DLM correction resulted in considerable changes in trim variables and aerodynamic pressure distribution outputs of static aeroelastic analysis. It is revealed by dynamic aeroelastic stability analysis that there is no flutter issue within the flight envelope and the flutter speed is much greater than the dive speed. Dynamic response analyses indicated that the response of the aircraft dies out in a short time and the model shows a dynamically stable behavior.
Ankara International Aerospace Conference


Static and dynamic aeroelastic analysis of a very light Aircraft
Demirer, Halime Gül; Kayran, Altan; Department of Aerospace Engineering (2021-9-10)
Aircraft design processes need to ensure that the aircraft is aeroelastically stable within its operational envelope. This thesis presents an overview of the static aeroelastic, flutter and gust response analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. The methods to be used in the aeroelastic analysis of the VLA are tested on the AGARD 445.6 wing, and the results are in good agreement with the literature. Aeroelastic model corrections such a...
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...
In Flight Icing Simulations on Airfoils
Uğur, Nermin; Özgen, Serkan; Görgülü, İlhan; Tatar, Volkan (null; 2015-05-31)
It is crucial to predict the ice mass, shape and regions of the airframe which are prone to icing in order to design and develop de/anti-icing systems for aircraft and airworthiness certification . In the current study, droplet collection efficiency and ice shape predictions are performed using an originally developed computational tool for a wing tip for which experimental and numerical data are available. Ice accretion modeling consists of four steps in the developed computational tool: flow field solutio...
External geometry and flight performance optimization of turbojet propelled air to ground missiles
Dede, Emre; Tekinalp, Ozan; Department of Aerospace Engineering (2011)
The primary goal for the conceptual design phase of a generic air-to-ground missile is to reach an optimal external configuration which satisfies the flight performance requirements such as flight range and time, launch mass, stability, control effectiveness as well as geometric constraints imposed by the designer. This activity is quite laborious and requires the examination and selection among huge numbers of design alternatives. This thesis is mainly focused on multi objective optimization techniques for...
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...
Citation Formats
H. G. Demirer and A. Kayran, “Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft,” presented at the Ankara International Aerospace Conference, Ankara, Türkiye, 2021, Accessed: 00, 2022. [Online]. Available: