Adjoint-based design optimization of a hypersonic inlet

Başaran, Mehmet
The inlet is one of the most essential parts of a scramjet engine. Its performance heavily affects the overall performance of the engine. The conventional scramjet inlet designs consist of a combination of multiple flat ramps. As the number of ramps increases, the total pressure recovery increases. However, the length and the weight of the engine also increase. In this study, the total pressure recovery of a single-ramp scramjet inlet is improved by aerodynamic shape optimization. In addition, the mass flow rate of the inlet is also maximized to increase the thrust. While performing the multi-objective optimization, the static pressure at the exit of the inlet is constrained to provide robust combustion. SU2 software with its discrete adjoint-based optimization tool is employed. It is observed that the optimum inlet design obtained satisfies both the shock-on-lip and the shock-on-shoulder conditions.


Adjoint based optimization of supersonic converging diverging nozzle
Yerlikaya, Berkan; Tuncer, İsmail Hakkı; Department of Aerospace Engineering (2019)
The nozzle produces the required thrust for the vehicle in an aircraft or rocket engine by expanding and accelerating the exhaust gas. In this study, the thrust of a supersonic converging-diverging nozzle is optimized by using SU2 software and the adjoint-based optimization tool. During the design optimization procedure, the inlet area, the exit area and the length of the nozzle are kept constant. The main objective is to obtain the maximum thrust within the geometric limitations. In order to maximize the t...
Design optimization of an s-shaped subsonic intake using bayesian approach and bezier curves
Atasoy, Mete; Özyörük, Yusuf; Department of Aerospace Engineering (2022-5-26)
Engine is a prominent part for the systems of a cruise missile. Reliable and efficient engine performance significantly depends on the quality of the incoming airflow. In this thesis, the aerodynamic performance of a subsonic intake is improved by using open-source multi-task Bayesian optimization (MTBO) tool. The main difference of Bayesian approaches from other optimization methods is that it has information about all design space, along with the uncertainty value. The learning process in the Bayesian app...
Cooling performance investigation of a two-pass rib-roughened channel
Kavas, İsa; Kurtuluş, Dilek Funda; Yasa, Tolga; Department of Aerospace Engineering (2015)
The performance of the modern aero-engines is highly dependent on the turbine inlet gas temperature. The higher temperature leads to more compact and efficient machines. Additionally, specific fuel consumption of the engine is decreased for the same thrust rating. However, the turbine inlet temperatures of the today’s engines are already beyond the material structural limits. Hence, the turbine section must be cooled down to acceptable levels. Various types of cooling methods are typically applied to the ga...
Surrogate model based system identification and control of gas turbine engines
Ekinci, Sinan; Yavrucuk, İlkay; Department of Aerospace Engineering (2019)
The focus of this thesis is on small low-cost turbojet engines where the fuel flow is provided by a gear-type fuel pump rather than a more traditional fuel metering unit. The incorporation of such type of fuel flow actuation devices introduces additional nonlinearities into the modeling and control of the small turbojet engines. As an alternative solution, this thesis presents and applies online/offline parameter estimation and adaptive control methods to such sub-class turbojet engines. For the simulation ...
Parallel optimization of flapping airfoils in a biplane configuration for maximum thrust
Tuncer, İsmail Hakkı (2004-05-27)
Flapping airfoils in a biplane configuration are optimized for a maximum thrust production. A parallel Navier-Stokes solver on overset grids and a gradient based parallel optimization method are employed. The periodic flapping motion of airfoils in a plane configuration is described in a combined pitch and plunge. The pitch and plunge amplitudes and the phase shift between them are optimized for a range of flapping frequencies. It is shown that at low flapping frequencies, flapping airfoils in a biplane con...
Citation Formats
M. Başaran, “Adjoint-based design optimization of a hypersonic inlet,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.