Increasing the Effectiveness of a Vertical Stabilizer by Combining Pulsed Jet Actuation at the Leading Edge and the Rudder Hinge Line

Löffler, Stephan; Staats, Marcel; Grund, Thomas; Weiss, Julien

doi:10.2514/6.2018-2854

Cited by 4 publications

(5 citation statements)

References 10 publications

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“…By using the non-dimensional Equation ( 9), a switching frequency of f pulse ≈ 499.4 Hz is calculated. The actual measured frequency was f pulse = 498 Hz [28]. Furthermore the FO-PJA used in the VTP experiments also had a mass flow range where high switching frequencies ( f pulse = 1493 Hz) were dominant.…”

Section: Discussionmentioning

confidence: 99%

“…With the non-dimensional Equation (10), the estimated frequency would be f pulse ≈ 1483 Hz. In [28], there were also larger FO-PJAs implemented in the VTP model. The first-order frequency in that case was f pulse = 336 Hz while the second-order frequency was f pulse = 1014 Hz.…”

Section: Discussionmentioning

confidence: 99%

“…Due to geometrical limitations and the required flow control parameters (frequency and outlet velocity respectively momentum flow rate), the actuator geometry had to be folded. Results of wind-tunnel experiments with this configuration of FO-PJA are provided in [28][29][30]. The main difficulty in the design process of the complex FO-PJA system is to build an actuator that will fit into a specific aerodynamic geometry of a given size while simultaneously fulfilling the required flow control parameters.…”

Section: Example Of Fo-pjas Used In Practicementioning

confidence: 99%

“…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%

See 3 more Smart Citations

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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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Section: Example Of Fo-pjas Used In Practicementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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

Löffler

Ebert

Weiss

2021

Fluids

Self Cite

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“…The experimental results show that the impact of an unsteady jet on restraining flow separation is better than that of a steady jet. The scholars Loeffler and Scholz et al, (2020) [20][21][22] in Germany carried out active flow control at the leading edge and stabilizer hinge increasing the vertical tail lateral force, the under different slip angles and rudder deflection angles. The experimental results show that active flow control at the front edge of the vertical tail stabilizer can significantly improve the flow separation on the stabilizer surface at large lateral slip angles, while reducing resistance.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Vertical Tail Model Flow Control Based on Oscillating Jet

Cao

Dong

et al. 2023

Applied Sciences

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In this paper, wind tunnel experiments are conducted to study the control law and mechanism of oscillating jet flow control to improve the aerodynamic characteristics of the vertical tail when a civil aircraft encounters left side gust or significant crosswind during takeoff and landing. We measured the vertical tail scaling model’s aerodynamics, spatial flow field, and surface pressure when the Reynolds number was 2.12 × 105. The maximum momentum coefficient of the oscillating jet actuator reaches 0.332%. In addition, we studied the flow control effect of the three-dimensional vertical tail scaled model in different spanwise positions. The experimental results show that the oscillating jet at the rear edge of the stabilizer can significantly increase the lateral force of the vertical tail, and the increment of the lateral force can reach 36.5% under the worst condition of the negative side slip angle of the vertical tail. We can improve the lateral force coefficient of the vertical tail model by applying flow control alone at different spanwise locations. The wing root’s control effect and the vertical tail’s middle section are better than the wing tip’s. The oscillating jet can effectively restrain the flow separation on the rudder. In addition, the input of a high-energy jet “ejects” the mainstream, which increases the flow velocity at the side of the vertical tail actuator. It increases the circulation of the vertical tail. The oscillating jet flow control technology can effectively improve the vertical tail’s steering efficiency and increase the vertical tail’s lateral force, which is of great significance in improving the safety and economy of civil aircraft.

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Circulation Control Experiments on a Vertical Tail

Singh

Scholz

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Increasing the Effectiveness of a Vertical Stabilizer by Combining Pulsed Jet Actuation at the Leading Edge and the Rudder Hinge Line

Cited by 4 publications

References 10 publications

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

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

Experimental Study of Vertical Tail Model Flow Control Based on Oscillating Jet

Circulation Control Experiments on a Vertical Tail

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