Automation and verification of Ankara wind tunnel

Katırcı, Argün
All the operational and measurement systems of Ankara Wind Tunnel was modified to operate automatically under the control of a central computer system programmed using the Lab View programming language. A cruciform air-to-air missile with triangular canard control and a trapezoidal wing model was tested by a 35mm diameter internal balance at Mach 0.2 and data was compared with the test data of the same model’s test that was performed at NASA Langley Research Center.


A tool for designing robust autopilots for ramjet missiles
Kahvecioğlu, Alper; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2006)
The study presented in this thesis comprises the development of the longitudinal autopilot algorithm for a ramjet powered air-to-surface missile. Ramjet Missiles have short time-of-flight, however they suffer from limited angle of attack margins due to poor operational-region characteristics of the ramjet engine. Because of such limitations and presence of uncertainties involved, Robust Control Techniques are used for the controller design. Robust Control Techniques not only provide an easy limitation/uncer...
Navigation algorithms and autopilot application for an unmanned airvehicle
Kahraman, Eren; Alemdaroğlu, Hüseyin Nafiz; Nalbantoğlu, Volkan; Department of Aerospace Engineering (2010)
This study describes the design and implementation of the altitude and heading autopilot algorithms for a fixed wing unmanned air vehicle and navigation algorithm for attitude and heading reference outputs. Algorithm development is based on the nonlinear mathematical model of Middle East Technical University Tactical Unmanned Air Vehicle (METU TUAV), which is linearized at a selected trim condition. A comparison of nonlinear and linear mathematical models is also done. Based on the linear mathematical model...
Fluid structure coupled analysis of an aerodynamic surface
Sümer, Bülent; Akgün, Mehmet A.; Department of Aerospace Engineering (2004)
In this thesis a 3-D Euler flow solver is coupled with a finite element program in order to solve static aeroelastic problems involving aircraft wings. A loosely coupled solution approach based on an iterative solution procedure is used to solve the coupled field problem. Because of the deformation of the underlying surface over which the flow is solved, Computational Fluid Dynamics mesh has to move at each computational aeroelastic iteration in order to comform to the new shape of the aerodynamic surface. ...
Design and performance analysis of a variable pitch axial flow fan for Anakara wind tunnel
Yalçın, Levent; Akmandor, İbrahim Sinan; Department of Aerospace Engineering (2006)
In this study, a variable pitch axial flow fan is designed and analysed for Ankara Wind Tunnel (AWT). In order to determine the loss caharacteristics of AWT, an algorithm is developed and the results are validated. Also some pressure and velocity measurements are made at the fan section to find the losses experimentally. After completion of the fan design, analyses are made at different volumetric flowrates and blade angles including the design point and the performance characteristics of the fan are obtain...
Development of a wing design tool using euler/navier-stokes flow solver
Ülker, Kıvanç; Akmandor, İbrahim Sinan; Department of Aerospace Engineering (2005)
A three dimensional wing design tool with analysis functions has been developed with embedded Euler/Navier-Stokes flow solver and a three dimensional hyperbolic grid generator. A graphical user interface has been constructed using PYTHON script language and the tool was enhanced with pre-processing and post-processing capabilities. Analysis and design procedures are demonstrated with automatic grid generation, automatic series solution and automatic graphs and reports generation.
Citation Formats
A. Katırcı, “Automation and verification of Ankara wind tunnel,” M.S. - Master of Science, Middle East Technical University, 2006.