Analysis of unsteady flows past oscillating wings

This thesis presents a more accurate and efficient method for the study of finite span wings in steady and unsteady supersonic flows with more computing efficiency.; For steady flows, the boundary conditions are expressed in terms of the source distributions over wing surfaces. Specific theoretical solutions are derived for the calculations of pressure coefficient distribution and the lift, pitching moment, and rolling moment coefficients. The present solutions have been validated for delta and trapezoidal wings by comparison with high order conical flow results based on the theory developed by Carafoli, Mateescu, and Nastase. An excellent agreement was found between these results.; For unsteady flows, the boundary conditions of finite span wings are modeled by using pulsating sources distributing over the wing surface. The present method leads to more accurate solutions for rigid wings executing harmonic oscillations in translation, pitching rotation, and rolling rotation of various oscillating frequencies. These solutions were found in very good agreement with the available high order conical flow solutions obtained by Carafoli, Mateescu, and Nastase.; Then the method has been used to obtain solutions for the flexible wings executing flexural oscillations, which are of interest for the aeroelastic studies in the aeronautical applications.