The DLR Project LamAiR: Design of a NLF Forward Swept Wing for Short and Medium Range Transport Application

Seitz, Arne; Kruse, Martin; Wunderlich, Tobias; Bold, Jens; Heinrich, Lars

doi:10.2514/6.2011-3526

Cited by 41 publications

(24 citation statements)

References 9 publications

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“…As a consequence, with an aft-swept wing, the design Mach number is limited to 0.74 [19] in order to avoid high wave drag. This was the motivation to develop the NLF forward swept wing concept within the DLR project LamAiR [20,21]. The basic idea is that a forward swept wing exhibits an increase of sweep in chordwise direction due to the taper (see Figure 5), thus allowing for cruise Mach numbers ranging from 0.76 to 0.80, like for the Airbus A320.…”

Section: Design Studies and Demonstration Testsmentioning

confidence: 99%

Drag Reduction by Laminar Flow Control

et al. 2018

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Abstract:The Energy System Transition in Aviation research project of the Aeronautics Research Center Niedersachsen (NFL) searches for potentially game-changing technologies to reduce the carbon footprint of aviation by promoting and enabling new propulsion and drag reduction technologies. The greatest potential for aerodynamic drag reduction is seen in laminar flow control by boundary layer suction. While most of the research so far has been on partial laminarization by application of Natural Laminar Flow (NLF) and Hybrid Laminar Flow Control (HLFC) to wings, complete laminarization of wings, tails and fuselages promises much higher gains. The potential drag reduction and suction requirements, including the necessary compressor power, are calculated on component level using a flow solver with viscid/inviscid coupling and a 3D Reynolds-Averaged Navier-Stokes (RANS) solver. The effect on total aircraft drag is estimated for a state-of-the-art mid-range aircraft configuration using preliminary aircraft design methods, showing that total cruise drag can be halved compared to today's turbulent aircraft.

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Section: Design Studies and Demonstration Testsmentioning

confidence: 99%

Drag Reduction by Laminar Flow Control

et al. 2018

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“…In the DLR project LamAiR [20] a multidisciplinary wing design of a forward swept wing with NLF and a composite structure including aeroelastic tailoring has been performed [22]. This aircraft configuration has been selected for the multidisciplinary wing optimization.…”

Section: Reference Aircraft Configurationmentioning

confidence: 99%

“…This study shows that the aircraft having an NLF wing design was not competitive against a turbulent wing design taking the top level aircraft requirements as a basis for comparison. In the DLR project LamAiR [20], however, the concept of forward sweep for laminar wings as proposed by Redeker and Wichmann [21] shows significant potential for efficiency improvements. In this project a multidisciplinary wing design of a forward swept wing having NLF and a composite structure including aeroelastic tailoring has been performed.…”

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Multidisciplinary optimization of an NLF forward swept wing in combination with aeroelastic tailoring using CFRP

et al. 2017

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This article introduces a process chain for commercial aircraft wing multidisciplinary optimization (MDO) based on high fidelity simulation methods. The architecture of this process chain enables two of the most promising future technologies in commercial aircraft design in the context of MDO. These technologies are natural laminar flow (NLF) and aeroelastic tailoring using carbon fiber reinforced plastics (CFRP). With this new approach the application of MDO to an NLF forward swept composite wing will be possible.The main feature of the process chain is the hierarchical decomposition of the optimization problem into two levels. On the highest level the wing planform including twist and airfoil thickness distributions as well as the orthotropy direction of the composite structure will be optimized. The lower optimization level includes the wing box sizing for essential load cases considering the static aeroelastic deformations. Additionally, the airfoil shapes are transferred from a given NLF wing design and the natural laminar flow is considered by prescribing laminar-turbulent transition locations.

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“…A similar comparison has also been made for a realistic 3D configuration (wing, fuselage, horizontal and vertical stabilizer) to check if the fuselage, which is long relative to c re f , has a negative influence on the achieved global loads. The so called LamAIR configuration has been selected [14], a configuration with forward swept wing and similar design mission like Airbus A320. The meshing philosophy used is the same, like in the 2D example.…”

Section: Gust Load Prediction Methodology For Industrial Environmentmentioning

confidence: 99%

Simulation of Interaction of Aircraft with Gust and Resolved LES-Simulated Atmospheric Turbulence

Kelleners¹,

Heinrich²

2015

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Conventionally for computation of aircraft performance uniform parallel flow at the far field of the simulation method is assumed and disturbances as present in the real earths atmosphere are neglected. To study and to recognize challenging aspects of the interaction of aircraft with disturbed oncoming flow two different simulation methods are developed and solutions computed are compared. The first method models the atmospheric disturbance, simulates the influence of this disturbance on the aircraft however neglects influence of the aircraft on the atmospheric disturbance. The second high-fidelity method resolves the disturbed oncoming flow and simulates full two-way interaction between disturbed atmosphere and the flying aircraft. Solutions computed are used to cross-check the predictions. The high-fidelity method is then used to simulate flight through resolved atmospheric turbulence.

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The DLR Project LamAiR: Design of a NLF Forward Swept Wing for Short and Medium Range Transport Application

Cited by 41 publications

References 9 publications

Drag Reduction by Laminar Flow Control

Drag Reduction by Laminar Flow Control

Multidisciplinary optimization of an NLF forward swept wing in combination with aeroelastic tailoring using CFRP

Simulation of Interaction of Aircraft with Gust and Resolved LES-Simulated Atmospheric Turbulence

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