A Low Subsonic Study of the NASA N2A Hybrid Wing-Body Using an Inviscid Euler-Adjoint Solver

Almosnino, D.

doi:10.2514/6.2016-3267

Cited by 5 publications

(18 citation statements)

References 22 publications

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“…Current research activities on BWB demonstrate that the coupling of high fidelity aerodynamics (Eulerian-or RANS-based) with optimization procedures can improve BWB aircraft (drag) performances [4,6,7]. Specifically, trade-offs between aerodynamics, stability and structural constraints enable new design solutions, eventually driving to drag reduction [4].…”

Section: Introductionmentioning

confidence: 99%

“…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%

“…Although several previous CFD studies on BWB are available at cruise speed conditions [2,3,[11][12][13], research literature shows that subsonic aerodynamics need to be further investigated, especially at approach and landing speeds. Two CFD tools, namely ANSYS-FLUENT and SU2 (v7.2.0 Blackbird), are adopted and compared with both experimental wind tunnel (WT) data and with other CFD simulations available in literature [6,14]. SU2 code is gaining a growing attention from the research community focused on aerodynamic design.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

et al. 2022

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“…This enables multiple solutions to be easily computed, without the need to regenerate meshes manually. In the early stages of vehicle design, inviscidflow Euler CFD solvers are used extensively across industry and academia [137], as they are often able to capture the trends in the aerodynamics of a launch vehicle sufficiently well for preliminary design purposes, while having relatively short run times that make the generation of aerodynamic databases practicable. However, inviscid solvers naturally do not capture the aerodynamic forces on a vehicle due to viscous effects.…”

Section: Aerodynamic Analysismentioning

confidence: 99%

“…Cart3D is an inviscid Euler solver CFD package, designed for use during preliminary vehicle design and analysis [137]. Cart3D is computationally efficient and requires only a surface triangulation of the vehicle being analysed to initiate a simulation.…”

Section: Cart3dmentioning

confidence: 99%