Design of a Wind Tunnel Apparatus to Assist Flow and Aeroelastic Conrtol via Zero Net Mass Flow Actuators

Abstract

A plunging-pitching aeroelastic apparatus has been developed to experimentally test new devices for flow and aeroelastic control. The purpose of the experiment is twofold: i) the first phase investigates the aeroelastic behavior of a two-dimensional wing section in postflutter region, structurally and aerodynamically characterizing the aeroelastic model; ii) the subsequent experiment will be instrumental to test active flow control devices in both the pre-and post-flutter regimes. The design of the testing apparatus utilizes a linear and nonlinear cam spring system that allows testing at selected aeroelastic and flowfield conditions. The wing section is mounted to the aeroelastic test apparatus and tests have been conducted in the low speed Clarkson University Wind Tunnel Facility. Plunging and pitching accelerations of the wing during aeroelastic response have been recorded to study and compare the experimental results with the proposed mathematical models. Active flow control devices are bench tested and will be installed in a composite NACA 0018 airfoil at specified locations along the wing span. Zero net mass flow actuators (ZNMF) are considered in this research: ZNMF control devices, such as synthetic jets actuators (SJA) and frequency driven voice coils, are under investigation to demonstrate their ability to actively change the flowfield for improved aeroelastic wing performances. Numerical simulations have already demonstrated improved performance regarding flow and aeroelastic characteristics due to active flow control. Experimental investigation, numerical studies, and corresponding analytical models are provided and pertinent conclusions are discussed.

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“…designs that do not require heavy mechanical deflection surfaces. LCO refer to "flutter" behavior in UAV wings that manifest themselves as constant-amplitude oscillations (O'Donnell et al (2007)), which result from nonlinearities inherent in the aeroelastic dynamics of the UAV system (Satak et al (2012)). Due to these behaviors, the LCO would surpass the limiting safe flight boundaries of an aircraft (Rubillo et al (2005)) and could potentially lead to structural damage and catastrophes.…”