Aerospace Technology Demonstration: BLADE, the Flagship Laminar Flow Project within the Clean Sky Programme

Williams, Gareth

doi:10.4271/2017-01-2016

Cited by 7 publications

(3 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Lee and Jameson [15] conducted a gradient-based NLF wing design at a Mach number of 0.74 and the transition criteria were not included in their gradient evaluations and their research focused on the reduction of the wave drag. In a European Laminar Aircraft Demonstrator project [16,17], NLF technology has been investigated on a low sweep outer wing section on the large transport aircraft Airbus A340 in flight tests, in which the cruising Mach number was not published. Streit et al [18] and Seitz et al [12] investigated the feasibility of forward swept laminar wing design for the typical transport aircraft, A320-200, with a design Mach number is 0.78.…”

Section: Introductionmentioning

confidence: 99%

Balancing Laminar Extension and Wave Drag for Transonic Swept Wings

Zhu

Qin

2021

AIAA Journal

View full text Add to dashboard Cite

At transonic condition, the design of natural laminar flow (NLF) wing is challenging, as the extension of the laminar flow needs to be finely balanced with the potential wave drag increase. To achieve this balance, it is proposed to unlock the wing sweep and introduce three-dimensional (3-D) contour shock-control bump (SCB) in the optimization of NLF infinite swept wing aiming at total drag reduction. A 3-D Reynolds-Averaged Navier-Stokes flow solver is extended to incorporate laminar-turbulent transition prediction due to streamwise and crossflow instabilities. The flow solver is integrated in a gradient-based optimization framework. The transition criteria including streamwise and crossflow instabilities are coupled in the sensitivity calculation using a discrete adjoint solver. Transonic design optimization of the sectional profile and wing sweep angle is first conducted at a Mach number of 0.78. The optimization managed to alleviate the shock wave, reducing the pressure drag while it failed to extend the laminar flow. Further, a combined optimization of the wing with a parameterized SCB at the same condition is carried out. The optimized wing with SCB features a long favorable pressure gradient region and a low sweep angle which allows for a large proportion of laminar flow without significant pressure drag. The shock wave is controlled by the 3-D bump and the SCB has little effect on the upstream flow.

show abstract

Section: Introductionmentioning

confidence: 99%

Balancing Laminar Extension and Wave Drag for Transonic Swept Wings

Zhu

Qin

2021

AIAA Journal

View full text Add to dashboard Cite

show abstract

“…Recently, Hue et al [11][12] and Xu et al [13] conducted some experimental and computational research of transonic NLF wing. The up to date "Breakthrough Laminar Aircraft Demonstrator in Europe" (BLADE) project tried to move from the aerodynamic concepts of natural laminar flow through to its industrialization and operational demonstration at full scale [14] [15]. The flight test vehicle was based on an A340 with some structural changes to meet the need of natural laminar flow including the notably reduced sweep angle.…”

Section: Introductionmentioning

confidence: 99%

Shock Control of a Low-Sweep Transonic Laminar Flow Wing

Zhu

Qin

et al. 2019

AIAA Journal

View full text Add to dashboard Cite

This paper presents a combined experimental and computational study of a low-sweep transonic natural laminar flow (NLF) wing with shock control bumps (SCBs). A transonic NLF wing with a relatively low sweep angle of 20° was chosen for this study. To avoid the complexity of the flow introduced by perforated/slotted walls commonly used for transonic wind tunnel tests for reducing the wall interference, both experimental tests and computational simulations were conducted with solid wind tunnel wall conditions. This allows for like-to-like validation of the computational simulation.Optimization of the shock control bumps was first conducted to design the wind tunnel test model with bumps. Two critical parameters of the three-dimensional SCBs for shock control, i.e. bump crest * Professor of Aerodynamics, AIAA Associate Fellow, Corresponding Author.

show abstract

“…The project had its focus on wing technologies and configurations covering transport aircraft and business jets. One major outcome of the SFWA activities was the so-called Breakthrough Laminar Aircraft Demonstrator in Europe (BLADE) demonstrator, an Airbus project within the framework to flight-test experimental (natural) laminar-flow wing sections on an A340 from September 2017 onwards [3].…”

mentioning

confidence: 99%

Editorial for the CEAS Aeronautical Journal special edition on Smart Fixed Wing Aircraft, WP 1.2 “Load Control”

Krüger

König

2019

CEAS Aeronaut J

View full text Add to dashboard Cite

This special issue of the CEAS Aeronautical Journal summarizes articles describing results of the work package "Load Control", which was part of the Smart Fixed Wing Aircraft (SFWA) project, taking place in the framework of the European Clean Sky research programme. The editorial first gives a short overview over the Clean Sky framework and the SFWA project. Second, the articles of the special issue are shortly introduced.

show abstract

Aerospace Technology Demonstration: BLADE, the Flagship Laminar Flow Project within the Clean Sky Programme

Cited by 7 publications

References 0 publications

Balancing Laminar Extension and Wave Drag for Transonic Swept Wings

Balancing Laminar Extension and Wave Drag for Transonic Swept Wings

Shock Control of a Low-Sweep Transonic Laminar Flow Wing

Editorial for the CEAS Aeronautical Journal special edition on Smart Fixed Wing Aircraft, WP 1.2 “Load Control”

Contact Info

Product

Resources

About