ENSAERO [1], is a multidisciplinary code for computing the unsteady flow and associated aeroelastic responses of aerospace vehicles. The code simultaneously integrates the time-dependent Euler or thin-layer, Reynolds-averaged Navier-Stokes equations and the structural equations of motion using aeroelastically adaptive dynamic grids. The code can predict static and dynamic response for flexible ...

A new method identifies coupled fluid-structure system with a reduced set of state variables is presented. Assuming that the structural model is known a priori either from an analysis or a test and using linear transformations between structural and aeroelastic states, it is possible to deduce aerodynamic information from sampled time histories of the aeroelastic system. More specifically given...

High-Altitude Long-Endurance (HALE) aircraft have wings with high aspect ratios. During operations of these aircraft, the wings can undergo large deflections. These large deflections can change the natural frequencies of the wing which, in turn, can produce noticeable changes in its aeroelastic behavior. This behavior can be accounted for only by using a rigorous nonlinear aeroelastic analysis....

This paper presents a recently developed computational tool for aeroelastic analysis of aircraft performance. The computational tool couples a vortex-lattice code, Vorview, with an aeroelastic model that computes wing structural deflections under a combined coupled bending-torsion motion. The aeroelastic model of the wing structure is based on a one-dimensional structural dynamic theory using s...

Lateral nozzle forces are known to cause severe structural damage to any new rocket engine in development. Currently there is no fully coupled computational tool to analyze this fluid/structure interaction process. The objective of this study was to develop a fully coupled aeroelastic modeling capability to describe the fluid/structure interaction process during the transient nozzle operations....

In this paper, a new algorithm for system identification based on frequency response is presented. In this method, given a set of magnitudes and phases of the system transfer function in a set of discrete frequencies, a system of linear equations is derived which has a unique and exact solution for the coefficients of the transfer function provided that the data is noise-free and the degrees of...

In this paper, a new algorithm for system identification based on frequency response is presented. In this method, given a set of magnitudes and phases of the system transfer function in a set of discrete frequencies, a system of linear equations is derived which has a unique and exact solution for the coefficients of the transfer function provided that the data is noise-free and the degrees of...

A three-degrees of freedom (3-DOF) coupled numerical simulation technique for synchronously extracting 18 aerodynamic derivatives of bridge decks is proposed and evaluated in this study. Computations are performed with a finite volume unstructured computational flow dynamics (CFD) solver using two-dimensional (2D) hybrid meshes with fine near-wall resolution. The accuracy of the numerical model...

In this study, aeroelastic response and performance analyses have been conducted for a 5MW-Class composite wind turbine blade model. Advanced coupled numerical method based on computational fluid dynamics (CFD) and computational flexible multi-body dynamics (CFMBD) has been developed in order to investigate aeroelastic responses and performance characteristics of the rotating composite blade. R...