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JOURNAL OF AIRCRAFT Vol. 44, No. 4, July–August 2007 Plasma Actuators for Hingeless Aerodynamic Control of an Unmanned Air Vehicle Mehul P. Patel,∗ T. Terry Ng,† and Srikanth Vasudevan‡ Orbital Research Inc., Cleveland, Ohio 44103 and Thomas C. Corke§ and Chuan He¶ University of Notre Dame, Notre Dame, Indiana 46556 DOI: 10.2514/1.25368 The use of dielectric barrier discharge plasma actuators for hingeless flow control over a 47-deg 1303 unmanned combat air vehicle wing is described. Control was implemented at the wing leading edge to provide longitudinal control without the use of hinged control surfaces. Wind-tunnel tests were conducted at a chord Reynolds number of 4:12 105 and angles of attack ranging from 15 to 35 deg to evaluate the performance of leading-edge plasma actuators for hingeless flow control. Operated in an unsteady mode, the actuators were used to alter the flowfield over the lee-side wing to modify the aerodynamic lift and drag forces on the vehicle. Multiple configurations of the plasma actuator were tested on the lee side and wind side of the wing leading edge to affect the wing aerodynamics. Data acquisition included force-balance measurements, laser fluorescence, and surface flow visualizations. Flow visualization tests mainly focused on understanding the vortex phenomena over the baseline uncontrolled wing to aid in identifying optimal locations for plasma actuators for effective flow manipulation. Force-balance results show considerable changes in the lift and drag characteristics of the wing for the plasma-controlled cases compared with the baseline cases. When compared with the conventional traditional trailing-edge devices, the plasma actuators demonstrate a significant improvement in the control authority in the 15- to 35-deg angle-of-attack range, thereby extending the operational flight envelope of the wing. The study demonstrates the technical feasibility of a plasma wing concept for hingeless flight control of air vehicles, in particular, vehicles with highly swept wings and at high angles of attack flight conditions in which conventional flaps and ailerons are ineffective. Nomenclature angle of attack, deg wing span, m drag coefficient lift coefficient mean aerodynamic chord, m nondimensional frequency of the actuator modulation frequency, Hz streamwise extent of the separation zone, m Reynolds number based on the mean chord and freestream velocity Strouhal number based on the mean chord freestream velocity at the entrance to the test section, m=s distance from the leading edge, m spanwise distance from the centerline, m aerospace community. This is due to a sharp rise in the demand and applications for UAVs for both military and civilian operations. Active flow control is one such technology that holds considerable promise in advancing the aerodynamic performance and maneuvering of UAVs. The technology is based on the use of small-scale actuators that elicit desired changes in the flow state by altering the balance of flowfield energy using flow-manipulation methods. This allows for elimination or reduction of traditional control surfaces and other variable geometry for aerodynamic control. It can also be used to enhance the performance of traditional control surfaces or the operational flight envelope of air vehicles by providing controls at flight conditions in which conventional control surfaces are ineffective. The actuators can be passive or active and can be operated in an open-loop or closed-loop fashion, as desired for the given application. Flow control has been shown to control or promote boundary-layer transition, augment lift, reduce drag, or modify acoustic emissions [1]. The quest for efficient flow control for improved vehicle aerodynamics has led to the development of many ingenious actuators and control techniques over the years [1]. Examples of flow control include passive and active vortex generators [1,2], suction [3], blowing [4], oscillatory blowing/suction [5], synthetic jet actuators [6], and dielectric barrier discharge (DBD) plasma actuators [7], to name a few. Although there are a number of different types of flow control actuators, it is becoming increasingly clear that for an actuator to buy its way onto an air vehicle, it not only needs to demonstrate the ability to generate the forces necessary for control, but also an overall improvement in the aerodynamic and structural efficiencies of the vehicle, relative to the conventional control system. The DBD plasma actuator has received considerable attention over the recent years as a practical flow control device due to its simple lightweight design with no moving parts, low energy consumption, and because of its ability to generate momentum without the need for fluidic plumbing. There is a large body of work on the use of different plasma generation methods for flow control, including dc glow discharge, RF glow discharge, and dielectric barrier discharge [8]. The DBD = b = CD = CL = c = F = fmod = Lsep = Rec = St = U1 = x = y = I. Introduction TECHNOLOGIES that broaden the roles and capabilities of unmanned air vehicles (UAVs) are of significant interest to the Received 17 July 2006; revision received 26 April 2007; accepted for publication 27 April 2007. Copyright © 2007 by M. Patel and T. 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. †Chief Aerodynamicist, 4415 Euclid Avenue, Suite 500. Senior Member AIAA. ‡Aerospace Engineer, 4415 Euclid Avenue, Suite 500. Member AIAA. §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. 1264PDF Image | Plasma Actuators for Hingeless Aerodynamic Control of an Unmanned Air Vehicle
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