Analysis and uncertainty quantification of a hybrid laminar flow control system

Barklage, Alexander; Bekemeyer, Philipp; Bertram, Anna; Himisch, Jan; Radespiel, Rolf; Badrya, Camli

doi:10.2514/6.2022-2452

Cited by 5 publications

(1 citation statement)

References 27 publications

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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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Section: Introductionmentioning

confidence: 99%

Inverter prototype development for HLFC compressor applications

Bismark

Juchmann²,

Bertram³

2022

CEAS Aeronaut J

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Validation of Suction Velocity Analysis for Active Laminar Flow Control with Uncertainties

Barklage¹,

Seitz

Horn

et al. 2023

AIAA Journal

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This study provides a validation of a recently developed uncertainty quantification methodology for suction velocities with the example of a novel laminar flow control design referred to as a tailored skin single duct (TSSD) panel. The TSSD panel is located on the leading edge of a vertical fin model of an Airbus A320 that is designed to maintain and extend laminar flow over the fin by means of boundary-layer suction. The suction velocities are highly dependent on the local porosity, which is only partly known in practice; therefore, the associated uncertainties need to be quantified. This is achieved by combining experimental and numerical data. The experimental data are based on the wind-tunnel experiments on a full-scale Airbus A320 vertical fin equipped with the TSSD system performed in the large low-speed facility of the German–Dutch Wind Tunnels. The measurements also feature highly accurate mass flow measurements of the integral mass flow through the TSSD system that serve as a validation reference for the uncertainty analysis. Uncertainties are provided for the predicted and the measured total mass flows to validate the proposed method, and a good agreement is obtained. A sensitivity study reveals the most influential contributions to the variance of the computed suction velocities. Depending on the difference between plenum and outer pressure, either uncertainties in the pressure distribution or uncertainties in the porosity parameters dominate the variance of the suction velocity.

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