Viscous-Inviscid Analysis of Transonic Swept Wings using 2.5D RANS and Parametric Shapes

Kontogiannis, Alexandros; Parenteau, Matthieu; Laurendeau, Éric

doi:10.2514/6.2019-2116

Cited by 6 publications

(3 citation statements)

References 26 publications

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“…To account for viscous and compressibility effects, the Non-Linear Vortex Lattice Method (NL-VLM) [19,20,[23][24][25] is used. This method applies a correction to the local angle of attack of the VLM sections in order to get a local lift coefficient C l i nv equal to a two-dimensional lift coefficient C l v i s , which is provided by Reynolds-Averaged Navier-Stokes (RANS) simulations, experimental data, or as in this paper by manufactured lift curves.…”

Section: B Lifting Surface Model -Vortex Lattice Methodsmentioning

confidence: 99%

Stall Cell Prediction Using a Lifting-Surface Model

2021

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This paper investigates the use of a lifting surface method towards the study of lift cells on wings, thereby extending the lifting-line model proposed by Spalart. In particular, calculations are made with a 3D Vortex-Lattice Method (VLM) coupled with two-dimensional sectional lift versus angle of attack polar to include viscous effects. This viscous coupling allows to capture pre-and post-stall regimes, making it a Non-Linear Vortex Lattice Method (NL-VLM). Canonical cases are examined, such as infinite span wings and wings with elliptical lift distributions coupled with manufactured lift-curves. To achieve these goals, numerical artifacts are developed. One is to enable solutions over infinite span wings, while the other has been traditionally used to stabilise the numerical scheme in the form of added numerical dissipation. Various parametric studies are performed using Spalart's model and our proposed NL-VLM model. This paper identifies the limitations of both models. As found by Spalart, the lifting line mode suffers from robustness issues without the addition of a Gaussian filter, and the number of cells increases with the number of modes. In contrast the NL-VLM model converges with and without the use of artificial dissipation, without affecting the number of stall cells.

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Section: B Lifting Surface Model -Vortex Lattice Methodsmentioning

confidence: 99%

Stall Cell Prediction Using a Lifting-Surface Model

2021

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“…All optimization cases are implemented for infinite-span wings. Infinite-span wings are classified as one kind of 2.5D wings [39]. The whole wing is formed by a single airfoil, and the wingspan is set as infinite.…”

Section: Optimization Frameworkmentioning

confidence: 99%

Hybrid Laminar Flow Control Optimizations for Infinite Swept Wings

Shi

Lan

Yang

2023

International Journal of Aerospace Engineering

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Maintaining the laminar flow on surfaces through active control is a significantly promising technique for reducing fuel burn and alleviating environmental concerns in commercial aviation. However, there is a lack of systematic parameter studies for the hybrid laminar flow control (HLFC) together with natural laminar flow (NLF). To address this need, we optimize the infinite swept wings with different sweep angles and at various conditions, including different Mach numbers, Reynolds numbers, and lift coefficients. The Reynolds-averaged Navier-Stokes (RANS) solver coupled with the linear stability theory is applied for the laminar-turbulent transition prediction, and the traditional optimization method based on evolutionary algorithms is applied for laminar flow wing optimization. The optimization results found that HLFC is required when the NLF fails at a larger sweep angle (35°) and Reynolds number ( 20 × 10 6 ). The lower pressure peak with boundary-layer suction is found to delay the transition of the regional aviation condition. Besides, the pressure distribution of HLFC is similar to NLF results at the lower Reynolds number ( 10 × 10 6 ) or sweep angle (25°), i.e., a gentle negative pressure gradient near the leading edge and a small favorable pressure gradient behind it. Clarifying the characteristics of laminar flow wings will advance the application of the laminar flow technique within its field.

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“…In this scenario, affordable and less time-consuming numerical codes with robust numerical schemes and accurate domain discretizations are of fundamental importance to have a reliable design tool to feed Multidisciplinary Design Optimization (MDO) procedures [6,9,10]. With this in mind, the present study focuses on the aerodynamic analysis of a BWB prototype, namely N2A, at low-Mach number conditions with the aim to explore and assess the accuracy of flowfield simulations carried out with grids built with about 15 M cells (half body), suitable for MDO procedures.…”

Section: Introductionmentioning

confidence: 99%

Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

et al. 2022

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Reduction of atmospheric emissions is currently a mandatory requirement for aircraft manufacturers. Several studies performed on Blended Wing–Body configurations showed a promising capability of reducing fuel consumption by increasing, at the same time, passengers’ transport capabilities. Although several aerodynamic studies are available at transonic speeds, low-speed evaluations of aerodynamic performances of Blended Wing Body aircrafts are less investigated. In this framework, the present paper deals with the aerodynamic performance of the N2A aircraft prototype at low-Mach number conditions. Aircraft longitudinal aerodynamics is addressed at M∞=0.2 with steady state three-dimensional RANS simulations carried out at two Reynolds numbers equal to 6.60×106 and 1.27×108, respectively. The former refers to an experimental test campaign performed at NASA Langley 14-by-22 foot subsonic tunnel, while the latter is related to free-flight conditions close to an approach and landing phase. Flowfield simulations are performed using the Computational Fluid Dynamic code FLUENT and the SU2 open-source code, currently adopted for research applications. Numerical solutions are validated by using available experimental data with reference to lift, drag, pitching moment and drag polar estimations. Pre-stall and post-stall aerodynamic behaviour through mean flow-field visualization along with the comparison of pressure distributions at several AoAs is addressed. Furthermore, the effect of convective discretization on a numerical solution for SU2 is discussed. Results indicate a good agreement with available experimental predictions. The present study aims to bridge existing computations at a Eulerian low-Mach number, with RANS computations and constitutes a further test-case for SU2 code with respect to a full aircraft configuration.

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Viscous-Inviscid Analysis of Transonic Swept Wings using 2.5D RANS and Parametric Shapes

Cited by 6 publications

References 26 publications

Stall Cell Prediction Using a Lifting-Surface Model

Stall Cell Prediction Using a Lifting-Surface Model

Hybrid Laminar Flow Control Optimizations for Infinite Swept Wings

Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

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