Design of a pulsed jet actuator for separation control

Schlösser, Philipp; Bauer, Matthias

doi:10.1007/s13272-018-0328-x

Cited by 8 publications

(6 citation statements)

References 15 publications

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“…With the underlying design, no moving parts are required which is a major benefit for the safety-driven aviation industry. A detailed explanation of the actuator and its multi-step design process are published in [20]. Flow control systems applying the same two-stage design were previously successfully tested and published in [6,8].…”

Section: Active Flow Control Systemmentioning

confidence: 99%

“…shows a correlation of the momentum coefficient and the mass flow supplied to the flow control system obtained from bench-top experiments. The derivation of the underlying formulae for the momentum coefficient c µ = fun 1 (ṁ,u ∞ ) and the velocity ratio VR = fun 2 (ṁ,u ∞ ), both as functions of the mass flowṁ and the free-stream velocity u ∞ , is detailed in[20]. Thick curves inFig.…”

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confidence: 99%

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Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Schloesser

Soudakov

Bauer³

et al. 2019

AIAA Journal

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Section: Active Flow Control Systemmentioning

confidence: 99%

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confidence: 99%

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Schloesser

Soudakov

Bauer³

et al. 2019

AIAA Journal

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“…Conveniently, the leading edge (LE) of the disturbed area can house these devices where slats do not exist directly downstream of the pylon. The implementation of AFC devices in the wing-pylon junction has been examined in past efforts as part of the EU AFLoNext project [16], where pulsed jet actuators (PJA) and Synthetic Jet Actuators (SJA) were simulated, installed [17] and tested. These tests showed promising results, but the high mass flow consumption (of PJA) and the insufficient momentum provided (by the SJA), call for a different device to be used.…”

Section: Figure 1 Cfd Simulation Of Wing-nacelle Junction Showing Flmentioning

confidence: 99%

Suction and pulsed blowing for control of local wing-engine-slat-cut out flow separation: The INAFLOWT Project

Shay

Posti

Mizrahi

et al. 2020

Aiaa Aviation 2020 Forum

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An experimental study on the application of active flow control (AFC) to a 1:8.4 scale model of a swept wing in a landing configuration was conducted. The wing is fitted with an Ultra High Bypass Ratio (UHBR) engine nacelle. The highly efficient UHBR engines characterized by a large diameter that interferes with the flow around the wing, degrading its performance. An innovative active flow control device, creating steady suction and pulsed blowing (PB), was installed in the leading-edge region of the wing, above the nacelle, and its performance was experimentally evaluated. The effects of the suction and PB mechanisms were examined individually and simultaneously, using relevant normalized parameters to pave the way to a full-scale wind tunnel test. It was shown that the AFC devices increase the lift by up to 3%, redirected the flow to the desired downstream direction and reduced the size of the separation zone created due to the implementation of the UHBR nacelle. The next step is validating the small-scale results of this study in full-scale wind tunnel tests that hopefully make the technology flight test ready.

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“…The latter was implemented with a fluid oscillator. Furthermore, the two-stage actuator design was adapted and optimized to control the flow separation at the pylon-wing junction of a real-scale model [26,27]. Later on, single-stage FO-PJAs were also used to control the three-dimensional (3D) flow separation on a vertical tail model [28][29][30].…”

Section: Introductionmentioning

confidence: 99%

Fluidic-Oscillator-Based Pulsed Jet Actuators for Flow Separation Control

Löffler

Ebert

Weiss

2021

Fluids

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The control of flow separation on aerodynamic surfaces remains a fundamental goal for future air transportation. On airplane wings and control surfaces, the effects of flow separation include decreased lift, increased drag, and enhanced flow unsteadiness and noise, all of which are detrimental to flight performance, fuel consumption, and environmental emissions. Many types of actuators have been designed in the past to counter the negative effects of flow separation, from passive vortex generators to active methods like synthetic jets, plasma actuators, or sweeping jets. At the Chair of Aerodynamics at TU Berlin, significant success has been achieved through the use of pulsed jet actuators (PJA) which operate by ejecting a given amount of fluid at a specified frequency through a slit-shape slot on the test surface, thereby increasing entrainment and momentum in a separating boundary layer and thus delaying flow separation. Earlier PJAs were implemented using fast-switching solenoid valves to regulate the jet amplitude and frequency. In recent years, the mechanical valves have been replaced by fluidic oscillators (FO) in an attempt to generate the desired control authority without any moving parts, thus paving the way for future industrial applications.

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Design of a pulsed jet actuator for separation control

Cited by 8 publications

References 15 publications

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Active Separation Control at the Pylon-Wing Junction of a Real-Scale Model

Suction and pulsed blowing for control of local wing-engine-slat-cut out flow separation: The INAFLOWT Project

Fluidic-Oscillator-Based Pulsed Jet Actuators for Flow Separation Control

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