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JOURNAL OF AIRCRAFT Vol. 44, No. 2, March–April 2007 CL= CL;max = c= F= f= L=D = Lsep = Re= Rechord = Sr= t= U1= x= = stall = Nomenclature coefficient of lift maximum coefficient of lift airfoil chord length nondimensional frequency of actuator modulation frequency of actuator ratio of lift to drag extent of flow separation Reynolds number Reynolds number based on length c Strouhal number airfoil maximum thickness freestream velocity distance measured from the leading edge angle of attack, deg stall angle, deg Introduction improvements in maneuverability, turn rates, glide range and payload, and reductions in takeoff/landing distance and field length requirements. Although the benefits of high-lift devices are well documented in the open literature, it is also known that the use of movable control surfaces increases airframe noise and vibration, especially at high deflection angles. At these conditions, most of the noise originates from the separated flow in the gap regions which contribute to the form drag component of the viscous drag of the wing. At off-design conditions, in particular, the drag penalty from these devices is very high. By present estimates used in the wing and tail design, eliminating the hinge gaps would result in a 10% drag decrease [1]. Another drawback of movable control surfaces is that a deploy and retract mechanism is required, which adds volume, weight, and cost to the high-lift system. To enhance the aerodynamic and structural performance of the air vehicle, it is therefore desired to either fully replace the traditional movable control surfaces with hingeless devices that retain/improve the aerodynamic effects, or limit their deflection angles, without compromising lift performance. Owing to the rapid growth in instrumentation, materials, and control technologies, the roles and capabilities of flow control and aerostructures are evolving. The use of smart aerostructures that can react rapidly to changing flow conditions to improve the aerodynamic and structural efficiencies of aircraft is gaining momentum. It is envisioned that future air vehicle designs will involve surfaces that shelter an integrated system of sensors, flow- control actuators, and feedback controllers that are able to adapt to unpredictable conditions (structural damage, wind shear, stall/spin, etc.) and reconfigure themselves in flight to regain/enhance control. This is the theme of the present work—the design of a smart aerostructure (slat) that can be used as an intelligent high-lift device with no moving parts. This work presents the concept and experimental evaluation of a smart plasma slat: a low-drag, hingeless, high-lift device which uses a sensor, an aerodynamic plasma actuator, and a feedback controller for autonomous sense and control of leading-edge flow separation and wing stall. This paper reports follow on work towards the application of a (single-dielectric-barrier discharge) plasma actuator as a performance-enhancing device for a high-lift system. Previously, the effects of an “open-loop” plasma slat and plasma Autonomous Sensing and Control of Wing Stall Using a Smart Plasma Slat Mehul P. Patel∗ and Zak H. Sowle† Orbital Research, Inc., Cleveland, Ohio 44103-3733 and Thomas C. Corke‡ and Chuan He§ University of Notre Dame, Notre Dame, Indiana 46556 DOI: 10.2514/1.24057 The concept of a self-governing smart plasma slat for active sense and control of flow separation and incipient wing stall is presented. The smart plasma slat design involves the use of an aerodynamic plasma actuator on the leading edge of a two-dimensional NACA 0015 airfoil in a manner that mimics the effect of a movable leading-edge slat of a conventional high-lift system. The self-governing system uses a single high-bandwidth pressure sensor and a feedback controller to operate the actuator in an autonomous mode with a primary function to sense and control incipient flow separation at the wing leading edge and to delay incipient stall. Two feedback control techniques are investigated. Wind tunnel experiments demonstrate that the aerodynamic effects of a smart actuator are consistent with the previously tested open-loop actuator, in that stall hysteresis is eliminated, stall angle is delayed by 7 deg, and a significant improvement in the lift-to-drag ratio is achieved over a wide range of angles of attack. These feedback control approaches provide a means to further reduce power requirements for an unsteady plasma actuator for practical air vehicle applications. The smart plasma slat concept is well suited for the design of low-drag, quiet, high- lift systems for fixed-wing aircraft and rotorcraft. HIGH-LIFT systems play an important role in the design of air vehicles. The wings on most modern-day air vehicles are equipped with high-lift systems, generally in the form of leading- edge slats and trailing-edge flaps. These devices have been shown to enhance the aerodynamic performance of air vehicles through increasing the maximum coefficient of lift, lift-to-drag ratio, and stall angle. Advantages of such performance-enhancing devices include Received 20 March 2006; revision received 1 August 2006; accepted for publication 1 August 2006. Copyright © 2006 by M. P. Patel and T. C. Corke. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 0021-8669/07 $10.00 in correspondence with the CCC. ∗Director, Aerodynamics Group, 4415 Euclid Avenue, Suite 500. Senior Member AIAA. †Aerospace Engineer, 4415 Euclid Avenue, Suite 500. ‡Clark Chair Professor, Aerospace and Mechanical Engineering Department, 101 Hessert Laboratory for Aerospace Research. Associate Fellow AIAA. §Ph.D. Candidate, Aerospace and Mechanical Engineering Department, 101 Hessert Laboratory for Aerospace Research. 516PDF Image | Autonomous Sensing and Control of Wing Stall Using a Smart Plasma Slat
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