Verification of a chamberless HLFC design with an outer skin of variable porosity

Kilian, Thomas; Horn, Matthias

doi:10.1007/s13272-021-00528-4

Cited by 4 publications

(2 citation statements)

References 8 publications

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“…This would make an HLFC system with only one large suction chamber or plenum possible. The functionality of this one-chamber approach has been validated by DLR in a large scale wind tunnel test [9]. If a laser-drilling process is used to produce the microperforated suction sheet, the easiest method for varying the porosity is to vary the hole pitch.…”

Section: Hlfc Design Requirementsmentioning

confidence: 99%

Some Specific Challenges of HLFC Design on a Long-Range Wing

Schrauf,

Kilian

2023

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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We describe the aerodynamic design of an HLFC system for the wing of a large transport aircraft and compare it to the the HLFC system installed in the VTP of the DLR A320 ATRA aircraft. For the VTP we used the ALTTA-design with a laser-drilled microperforated titanium sheet with only one microperforation and small suction chambers beneath it. For the wing we designed a system with only one large plenum and controlled the suction with the help of variable microperforation. Some specific challenges of an HLFC design on a wing in contrast to a VTP application are highlighted here.

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Section: Hlfc Design Requirementsmentioning

confidence: 99%

Some Specific Challenges of HLFC Design on a Long-Range Wing

Schrauf,

Kilian

2023

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…HLFC has already been advanced in several projects, for example by wind-tunnel tests [2], flight tests [3,4] or general design considerations [5][6][7][8][9]. Within the EU-funded Clean Sky 2 program, research is done for enabling HLFC on the Horizontal Tailplane (HTP) [10] and the wing [11] of an aircraft similar to the Airbus A330.…”

Section: Introductionmentioning

confidence: 99%

Inverter prototype development for HLFC compressor applications

Bismark

Juchmann²,

Bertram³

2022

CEAS Aeronaut J

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A key component in Hybrid Laminar Flow Control (HLFC) is a turbo-compressor, which requires an inverter. However, a harsh environment in combination with restrictive boundary conditions make the inverter design very challenging. Moreover, aviation certification standards have to be considered. By reason of its growing significance, a Model-Based Systems Engineering (MBSE) approach is described to break the HLFC system requirements down to the lower level of the inverter. Using the acquired set of requirements, the design of an inverter prototype was initiated. For this, the compressor motor, a Permanent Magnet Synchronous Motor (PMSM) running up to 150,000 $$\text {min}^{\text {-1}}$$ min -1 at a power of more than 5 kW, was characterized by measurements. Thereafter, a control concept was elaborated and implemented on a preliminary electronics. In the end, feasibility tests were conducted on a testbed, whose results match well with the theory.

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