Numerical investigations of lateral jets for missile aerodynamics

Ağsarlıoğlu, Ekin
In this thesis, effects of sonic lateral jets on aerodynamics of missiles and missilelike geometries are investigated numerically by commercial Computational Fluid Dynamics (CFD) software FLUENT. The study consists of two parts. In the first part, two generic missile-like geometries with lateral jets, of which experimental data are available in literature, are analyzed by the software for validation studies. As the result of this study, experimental data and CFD results are in good agreement with each other in spite of some discrepancies. Also a turbulence model study is conducted by one of test models. It is also found out that k-ε turbulence model is the most suitable model for this kind of problems in terms of accuracy and ease of convergence. In the second part of the thesis, parametric studies are conducted on a generic supersonic missile, NASA TCM, to see the effect of jet parameters on missile and component force and moments in pitch plane. Variable parameters are jet location, jet mass flow rate and angle of attack. As a result, it was found out that downstream influence zone of jet exit is more than the upstream influence zone. Normal force occurring by the interaction of the free stream and jet plume are amplified whenever the jet exit is located between lifting surfaces. Greater pitching moments are obtained when the jet exit moment arm with respect to moment reference center or jet mass flow rate is increased.


Mathematical Modeling of the NOTAR Antitorque System for Flight Simulation
Yavrucuk, İlkay; Uzol, Oğuz (2013-04-01)
In this paper, a mathematical model of a helicopter NO TAil Rotor (NOTAR) antitorque system is developed for real-time flight simulations. The model consists of the circulation control tail boom, direct jet thruster, and the vertical stabilizers. The airflow inside the tail boom is modeled by dividing the flow into aerodynamic control volumes. The model features a bladeelement-type approach for modeling the mass flow through the axial fan blades as well as aerodynamic mass and momentum conservation calculat...
Aerodynamic design and performance analyses of grid fin in supersonic flow using design of experiments and computational fluid dynamics
Dinçer, Erdem; Sezer Uzol, Nilay; Department of Aerospace Engineering (2022-2)
Control surfaces are key components of missile aerodynamic performance that can create the necessary forces and moments to make maneuvers. Grid fins are unconventional control surfaces used for aerodynamic control of missiles. In this thesis, parametric design of grid fin is performed in terms of aerodynamic performance using Design of Experiments and Computational Fluid Dynamics. The 3-D, steady-state, compressible, viscous flow CFD simulations are performed for the complex grid fin geometries in supersoni...
Nonlinear Dynamic Inversion Autopilot Design for an Air Defense System with Aerodynamic and Thrust Vector Control
Bıyıklı, Rabiya; Yavrucuk, İlkay; Tekin, Raziye; Department of Aerospace Engineering (2022-2)
The study proposes complete attitude and acceleration autopilots in all three channels of a highly agile air defense missile by utilizing a subcategory of nonlinear feedback linearization methods Nonlinear Dynamic Inversion (NDI). The autopilot design includes cross-coupling effects enabling bank-to-turn (BTT) maneuvers and a rarely touched topic of control in the boost phase with hybrid control which consists of both aerodynamic fin control and thrust vector control. This piece of work suggests solut...
Computational Analysis of a Model Scale Helicopter Rotor in Ground Effect
Şahbaz, Mehmet; Sezer Uzol, Nilay; Kurtuluş, Dilek Funda (2017-09-22)
In this study, a numerical investigation of ground effect of a helicopter rotor is investigated with Computational Fluid Dynamics method. For this purpose, a model scale 2 bladed helicopter rotor is chosen. An experimental study is referred for comparison and validity of CFD method.
Adaptive control of guided missiles
Tiryaki Kutluay, Kadriye; Yavrucuk, İlkay; Department of Aerospace Engineering (2011)
This thesis presents applications and an analysis of various adaptive control augmentation schemes to various baseline flight control systems of an air to ground guided missile. The missile model used in this research has aerodynamic control surfaces on its tail section. The missile is desired to make skid to turn maneuvers by following acceleration commands in the pitch and yaw axis, and by keeping zero roll attitude. First, a linear quadratic regulator baseline autopilot is designed for the control of the...
Citation Formats
E. Ağsarlıoğlu, “Numerical investigations of lateral jets for missile aerodynamics,” M.S. - Master of Science, Middle East Technical University, 2011.