Conceptual aerodynamic design of ramjet missiles

Download
2017
Demiral, Ertan
The prediction of aerodynamic coefficients of missiles that have air-breathing components is a challenging task during the preliminary design phase. It is considerably important to estimate missile aerodynamic coefficients accurately at the beginning of design phase to avoid poor designs which could lead to redesign at later stages of the design process. In this study, firstly an improved method is developed to predict the aerodynamic coefficients of missile configurations with air-breathing components more accurately compared to engineering level fast prediction tools. Then, optimization studies comprising of reaching global minimum value of the Beale Function and inverse design optimization of the ramjet missile configuration are done through implementing different meta-heuristic optimization techniques which are “Genetic Algorithm”, “Differential Evolution” and “Modified Cuckoo Search”. In the inverse design optimization studies, two different methods, which are engineering level fast prediction tool Missile DATCOM and the improved method, are used to calculate aerodynamic coefficients of the candidate missile configurations throughout the design optimization process. Results of the inverse design optimization studies show that preliminary design phase of the missiles including air-breathing components can be enhanced significantly since accuracy of the prediction of aerodynamic coefficients is improved by methods applied in this study.

Suggestions

Numerical investigation of characteristics of pitch and roll damping coefficients for missile models
Kayabaşı, İskander; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2012)
In this thesis the characteristics of pitch and roll damping coefficients of missile models are investigated by using Computational Fluid Dynamics (CFD) techniques. Experimental data of NACA0012 airfoil, Basic Finner (BF) and Modified Basic Finner (MBF) models are used for validation and verification studies. Numerical computations are performed from subsonic to supersonic flow regimes. Grid refinement and turbulence model selection studies are conducted before starting the dynamic motion simulations. Numer...
Improving flow structure and natural convection within fin spacings of plate fin heat sinks
Özet, Mehmet Erdem; Tarı, İlker; Department of Mechanical Engineering (2015)
The main objectives of this thesis are to numerically investigate the previously observed recirculation zones and longitudinal vortices that occur in low fin height plate finned horizontal heat sinks and to improve the flow structures and heat transfer in these zones using various approaches with the help of simulations performed using commercially available CFD software. The approaches used for improvements are replacing the outer most fins with higher ones, introducing gaps on the length of the fins in va...
Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics
Dağlı, Efe Can; Aksel, M. Haluk.; Department of Mechanical Engineering (2019)
In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method us...
Analysis, design and test of a jet vane based thrust vector control for tactical missiles
Eren, Oğuz; Eyi, Sinan; Department of Aerospace Engineering (2017)
In this thesis, a design effort for a jet vane based Thrust Vector Control (TVC) in the scope of mechanical design, computational analysis and validating test process is executed to be able to find an optimum CFD approach to this kind of work. To do that, a preliminary design phase is initiated with an already optimized geometry which provides an aerodynamic surface to be worked on. After mechanical design approach to the geometry with system requirements, some of the unverified aspects of the design are te...
Three dimensional reacting flow analysis of a cavity-based scramjet combustor
Rouzbar, Ramin; Eyi, Sinan; Department of Aerospace Engineering (2016)
Scramjet engines have become one of the main interest areas of the supersonic propulsion systems. Scramjets are rather a new technology and they possess unsolved issues and problems regarding their operation, especially in the combustion process. Combustion at high speeds cause various problems as flame instability and poor fuel-air mixing efficiency. One of the methods used to overcome these problems is to recess cavity in the combustor wall where secondary flow is generated. In this study, a CFD tool is d...
Citation Formats
E. Demiral, “Conceptual aerodynamic design of ramjet missiles,” M.S. - Master of Science, Middle East Technical University, 2017.