Fluid-Structure Interactions in Highly Flexible Wings; Experimental campaigns and Development of a F
Abstract
This project focuses on the following research goals: (i) creating a fluid-structure interactions (FSI) high-resolution experimental, campaign for study and characterization of flow-induced instability of high aspect-ratio flexible wings, investigating the associat,ed three-dimensional (3D) flow physics and nonlinear structural dynamics of the system, and (ii) developing of a robust reduced- ord,er nonlinear FSI model by coupling nonlinear structural dynamics with 3D flow field information. The developed reduced-order model (,ROM) will facilitate studying the response of the flexible wing at high levels of maneuverability and different operational environm,ents.The main technical approaches that will be used to address the above objectives are: (i) through a set of both wind and water t,unnel experiments, we will investigate the FSI response and flow-induced instability characteristics of a high aspect-ratio flexible, wing at different angles of attack and flow velocities by measuring the nonlinear structural dynamics response of the system,(ii) w,e will conduct qualitative (Hydrogen bubble flow visualization for water tunnel and smoke flow visualization for wind tunnel) and qu,antitative (two-dimensional and volumetric Particle Tracking Velocimetry - PTV) flow measurements at different spanwise locations of, the flexible wing to understand the fundamental mechanisms of flow around the wing and the unsteady flow interaction with the flexi,ble body of the wing, and (iii) we will reconstruct the 3D flow field over the volume of a high aspect-ratio flexible wing from two-,dimensional snapshots of PTV, using a novel technique of Sectional Snapshot Optimization (SSO), introduced in this proposal. Once th,e 3D flow is recon- structed, we will incorporate this PTV-based 3D flow field information as an input to develop a flow physics-inf,ormed reduced-order nonlinear FSI framework to study the flow-induced instability of high aspect-ratio flexible wings. The FSI respo,nse characterization will be studied through wind tunnel experiments, and will be compared to similar experiments conducted in a den,ser fluid, water, using water tunnel experiments. Unsteady effects caused by the inertia of the accelerating fluid flow surrounding,the flexible wing, known as added mass, will be investigated on the flexible wings FSI response, motion kinematics, and lift capabi,lities.Upon successful completion of this project, the finding from this research are anticipated to impact scientific research and,naval aviation community by: (i) providing us with a detailed understanding of fluidelastic behavior of a high aspect-ratio flexible, wing in a wide range of possible operational environments, (ii) creating a robust methodology to study fully-coupled reduced-order,nonlinear fluid-structure interaction models for flexible wings, in which highly-resolved experiments are integrated into the model,, providing both a priori input and a posteriori validation for key terms in the model. The collected experimental data set along wit,h the developed FSI framework will leverage our understanding of flow-induced instability in flexible wings, that can be implemented, towards development of innovative and effective flow control strategies, that is detrimental to the aircraft performance and its st,ructural reliability.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Apr 01, 2022
- Source ID
- N000142212289
Entities
People
- Banafsheh Seyed-Aghazadeh
Organizations
- Office of Naval Research
- United States Navy
- University of Massachusetts