Özden, Aysu
Baran, Özgür Uğraş
Aksel, Mehmet Hâluk
Cold gas propulsion systems are mainly used for attitude controlof satellites.It is possible to obtainvery low pressure and temperature at the exit section of the nozzledue to propulsion system’s nature. Investigation of steady state performance of a cold gas thruster under real gas effects is decided to be carried out. SU2, an open source compressible CFD tool,is used for analyses ofideal gas, Peng-Robinson and van-der Waals gas models. Vacuum chamber test facility of Roketsan is usedfor performance tests. Results showed that van der Waals gas model in SU2is good enough for predictions of cold gas thruster’s performance.


Conceptual internal design and computational fluid dynamics analysis of a supersonic inlet
Alemdaroğlu, Mine; Özyörük, Yusuf; Department of Aerospace Engineering (2005)
In this thesis, the conceptual internal design of the air inlet of a supersonic, high altitude, solid propellant ramjet cruise missile is performed. Inviscid, compressible CFD analysis of the designed inlet is made in order to obtain qualitative and quantitative performance characteristics of the inlet at different operating conditions. The conceptual design of the inlet is realized by using analytical relations and equations, correlations derived from numerous available past experimental data and state-of-...
Performance characteristics of a cold gas thruster with real gas effects
Özden, Aysu; Aksel, M. Haluk.; Department of Mechanical Engineering (2019)
Cold gas propulsion systems are mainly used for attitude control purposes for space applications since 1960s due to their advantages in cost effectiveness, simplicity, availability, etc. It is important to investigate transient behavior of the thruster of these systems since they operate in a very short period of time, in the order of milliseconds. Both depressurization of the tank and expansion of thrusters to the vacuum, in order to obtain optimum performance in space, result into obtaining low temperatur...
Modelling of interaction of shock waves with analytical methods
Koç, Mesut; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2022-2)
In supersonic air vehicles, specially shaped air ducts are used to supply the air with required properties to the combustion chambers. Two-dimensional supersonic flow solvers used to design such geometrical shapes have become less accurate as the geometrical shape of the air duct becomes asymmetric or flow becomes three-dimensional. This problem can be overcome by solving the interaction between shock planes using analytical methods. In this study, an analytical solution model based on principles of gas dyn...
Passive flow control in liquid-propellant rocket engines with cavitating venturi
Ulaş, Abdullah (Elsevier BV, 2006-04-01)
In a companion liquid rocket engine development project, due to the overall weight constraint of the propulsion system, a cavitating venturi is selected to control the liquid fuel and liquid oxidizer mass flow rates. Two cavitating venturis, one for the fuel and the other for the oxidizer, are designed to deliver the desired mass flow rates for a specified operating inlet pressure, temperature, and inlet cross-sectional area. The converging and diverging angles of the venturis are selected from the literatu...
Aerodynamic design optimization using 3-dimensional euler equations and adjoint method
Yıldırım, Ali; Eyi, Sinan; Department of Aerospace Engineering (2017)
S-duct diffusers are often used for aircraft propulsion systems that convey the intake air to the engine compressor. In this thesis, flow structure at separated entrance conditions in an S-duct diffuser that designed for a micro turbojet engine powered aircraft is investigated using experimental and numerical methods. Flow characteristics such as flow separation, secondary flows, and swirl are investigated to find out the source of distortions and pressure loss at aerodynamics interface plane. Experiments a...
Citation Formats
A. Özden, Ö. U. Baran, and M. H. Aksel, “PERFORMANCE COMPARISON OF SU2 REAL GAS MODELS AND TESTING FOR A COLD GAS THRUSTER,” METU, Ankara, 2019, p. 1, Accessed: 00, 2021. [Online]. Available: