Active Flow Separation Control on a High-Lift Wing-Body Configuration Part 2: The Pulsed Blowing Application

Ciobaca, Vlad; Kühn, Timo; Rudnik, Ralf; Bauer, Matthias; Gölling, Burkhard

doi:10.2514/6.2011-3169

Cited by 6 publications

(3 citation statements)

References 16 publications

(15 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The application of the active flow control (AFC) technology can remedy this problem and allow more aggressive wing tip designs. The AFC has been successfully used by Fricke et al (2016) and Ciobaca et al (2011) to remedy the problem of flow separation and by Ciobaca and Wild (2014) for classical blended winglet.…”

Section: Introductionmentioning

confidence: 99%

Numerical studies of active flow control on wing tip extension

Vrchota¹,

Prachař²,

Peng

et al. 2019

AEAT

View full text Add to dashboard Cite

Purpose In the European project AFLoNext, active flow control (AFC) measures were adopted in the wing tip extension leading edge to suppress flow separation. It is expected that the designed wing tip extension may improve aerodynamic efficiency by about 2 per cent in terms of fuel consumption and emissions. As the leading edge of the wing tip is not protected with high-lift device, flow separation occurs earlier than over the inboard wing in the take-off/landing configuration. The aim of this study is the adoption of AFC to delay wing tip stall and to improve lift-to-drag ratio. Design/methodology/approach Several actuator locations and AFC strategies were tested with computational fluid dynamics. The first approach was “standard” one with physical modeling of the actuators, and the second one was focused on the volume forcing method. The actuators location and the forcing plane close to separation line of the reference configuration were chose to enhance the flow with steady and pulsed jet blowing. Dependence of the lift-to-drag benefit with respect to injected mass flow is investigated. Findings The mechanism of flow separation onset is identified as the interaction of slat-end and wing tip vortices. These vortices moving toward each other with increasing angle of attack (AoA) interact and cause the flow separation. AFC is applied to control the slat-end vortex and the inboard movement of the wing tip vortex to suppress their interaction. The separation onset has been postponed by about 2° of AoA; the value of ift-to-drag (L/D) was improved up to 22 per cent for the most beneficial cases. Practical implications The AFC using the steady or pulsed blowing (PB) was proved to be an effective tool for delaying the flow separation. Although better values of L/D have been reached using steady blowing, it is also shown that PB case with a duty cycle of 0.5 needs only one half of the mass flow. Originality/value Two approaches of different levels of complexity are studied and compared. The first is based on physical modeling of actuator cavities, while the second relies on volume forcing method which does not require detailed actuator modeling. Both approaches give consistent results.

show abstract

Section: Introductionmentioning

confidence: 99%

Numerical studies of active flow control on wing tip extension

Vrchota¹,

Prachař²,

Peng

et al. 2019

AEAT

View full text Add to dashboard Cite

show abstract

“…Aerospace companies such as Airbus and Boeing have researched the incorporation of fluidic oscillators (FOs) into wings and wing flaps to prevent flow separation. 1,2 In these studies, FOs were fastened to metal components with slots cut out of the thin aluminum skin to expose the jets to the free stream. While successful, all of these tests were conducted on airfoils constructed of metal components, rather than composite materials, which pose integration issues.…”

Section: Introductionmentioning

confidence: 99%

The design and manufacturing of fluidic oscillators for composite aircraft structures

Aly

Colton

2018

Proceedings of the Institution of Mechanical Engineers, Part B:

View full text Add to dashboard Cite

Active flow control devices have been proven to reduce drag and delay stall on commercial aircraft. This leads to lower fuel usage and thus reduced flight costs. However, there is a large uncertainty as to how to integrate active flow control devices into aircraft, specifically those with composite structures. In addition, the cost of manufacturing active flow control devices for large-scale production has not been previously studied. In this article, design concepts for the attachment of a fluidic oscillator to a composite aircraft structure are investigated. A systematic approach from the conceptual design to the final design is performed using different design tools. A cost analysis is performed to select the most cost-effective design configuration based on large volume fluidic oscillator production. Through design validation and cost estimation, the final design is shown to be feasible for large volume manufacturing.

show abstract

“…A significant effort of experimental and numerical investigation of the application of the passive and AFC techniques to locally suppress the flow separation or improve the high-lift performances at the wing-pylon area, outer-wing or applied to high-lift devices has been done [3][4][5][6][7]. This paper summarized the results of the SJA of the high-lift configuration using the CFD simulation by means of URANS approach.…”

Section: Introductionmentioning

confidence: 99%