Aerodynamic analysis of complex missile geometries ny panel methods

Önen, Cenk


Aerodynamic analysis of a full aircraft configuration using a panel method
Kurtuluş, Dilek Funda; Alemdaroğlu, Nazif; Özyörük, Yusuf; Department of Aeronautical Engineering (2002)
Aerodynamic design optimization of three dimensional rocket nozzles using adjoint method
Eyi, Sinan (null; 2013-09-13)
A design optimization method based on three dimensional Euler equations is developed. A finite volume method is implemented to discretize the Euler equations. Newton's method is used to solve the discretized form of Euler equations. Newton's method requires the calculation of the Jacobian matrix which is the derivative of the residual vector with respect to the flux vector. Different upwind methods are used in the calculation of flux vectors. Numerical and analytical methods are utilized in the evaluation o...
Aerodynamic optimization of turbomachinery cascades using Euler/boundary-layer coupled genetic algorithms
Oksuz, O; Akmandor, IS; Kavsaoglu, MS (American Institute of Aeronautics and Astronautics (AIAA), 2002-05-01)
A new methodology is developed to find the optimal aerodynamic performance of a turbine cascade. A boundary-layer coupled Euler algorithm and a genetic algorithm are linked within an automated optimization loop. The multiparameter objective function is based on the blade loading. For a given inlet Mach number and baseline cascade geometry, the flow inlet and exit angles, the blade thickness and the solidity are optimized by a robust genetic algorithm. First, the Sanz subcritical turbine cascade is selected ...
Aerodynamic parameter estimation of a missile in closed loop control and validation with flight data
Aydın, Güneş; Kutay, Ali Türker; Department of Aerospace Engineering (2012)
Aerodynamic parameter estimation from closed loop data has been developed as another research area since control and stability augmentation systems have been mandatory for aircrafts. This thesis focuses on aerodynamic parameter estimation of an air to ground missile from closed loop data using separate surface excitations. A design procedure is proposed for designing separate surface excitations. The effect of excitations signals to the system is also analyzed by examining autopilot disturbance rejection pe...
Aerodynamic analysis of flatback airfoils using vortex particle method
Haser, Senem Ayşe; Uzol, Oğuz; Department of Aerospace Engineering (2014)
In this thesis, aerodynamic analysis of flatback airfoils, which have been proposed and investigated to improve the aerodynamic performance of thick airfoils, is studied. Vortex particle method, which is commonly used for simulation of two dimensional, incompressible, viscous flows, is used for this purpose. In the content of this thesis, vortex particle method code developed by Kaya [1] is improved by changing method of diffusion and method of vorticity releasing from solid boundary. Deterministic Particle...
Citation Formats
C. Önen, “Aerodynamic analysis of complex missile geometries ny panel methods,” Middle East Technical University, 1996.