Design of a pulsed jet actuator for separation control
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ORIGINAL PAPER
Design of a pulsed jet actuator for separation control Philipp Schlösser1 · Matthias Bauer2 Received: 21 March 2018 / Revised: 3 September 2018 / Accepted: 12 September 2018 © Deutsches Zentrum für Luft- und Raumfahrt e.V. 2018
Abstract A pulsed jet actuator for separation control has been developed for application in a real-scale wind tunnel experiment with focus on separation behind the pylon-wing junction. This paper covers the last steps of hardware design and testing on the way to a successful demonstration of flow control at the pylon-wing junction. The concept of the actuator is based on fluidic technology and applies pulsed blowing without the help of moving parts. Design parameters are given by numerical simulations of the experimental application case and are validated in ground test. Results of these ground tests are presented and parameters for wind tunnel test settings are derived. The further evaluation of ground test results yields a relation of momentum coefficient, supply mass flow and wind tunnel velocities. It is shown that for the given wind tunnel experiment levels of constant momentum coefficient approximately coincide with levels of constant velocity ratio. All requirements with respect to flow control parameters and model geometry can be satisfied with the presented design, paving the way for a successful demonstration of flow control in a large-scale wind tunnel test. Keywords Active flow control · Separation control · Pulsed jet actuator Abbreviations Acronyms AFC Active flow control CFD Computational fluid dynamics Latin c𝜇 Momentum coefficient c Chord length DC Duty cycle F + Normalized frequency f Frequency I Momentum flux ṁ Mass flow M Mach number q Dynamic pressure This paper is part of a Special Issue on AFLoNext “Active Flow, Loads & Noise control on next generation wing”, funded by the EC’s FP7 under grant agreement no 604013. * Philipp Schlösser [email protected] Matthias Bauer [email protected] 1
Airbus Defence and Space GmbH, 81663 Munich, Germany
Navasto GmbH, Reuchlinstr. 10‑11, Aufgang H, 10553 Berlin, Germany
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R Specific gas constant S Surface area T Temperature u Velocity VR Velocity ratio Greek 𝛾 Ratio of specific heats 𝜌 Density Subscripts AFC AFC system property jet AFC jet property peak Maximum value ref Reference property 0 Stagnation property ∞ Ambient/free-stream condition
1 Introduction Separation of air flow over an aerodynamic surface is usually undesirable. The functional limit of an aircraft wing is given by separation on large sections of the wing, commonly known as stall. Active flow control (AFC) is a trending technology that can potentially enhance the performance of aircraft and was recently demonstrated in flight test with
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separation control applied to the vertical stabilizer of an airliner [1]. Previously, the potential of AFC has been proven in wind tunnel tests with a variety of different control systems [2–4]. This paper describes the design and devel
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