NDLI: Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

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Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

Content Provider	MDPI
Author	Aprovitola, Andrea Aurisicchio, Francesco Nuzzo, Pasquale Emanuele Di Pezzella, Giuseppe Viviani, Antonio
Copyright Year	2022
Abstract	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 $M_{\infty} = 0.2$ with steady state three-dimensional RANS simulations carried out at two Reynolds numbers equal to $6.60 \times 10^{6}$ and $1.27 \times 10^{8}$ , 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.
Starting Page	89
e-ISSN	22264310
DOI	10.3390/aerospace9020089
Journal	Aerospace
Issue Number	2
Volume Number	9
Language	English
Publisher	MDPI
Publisher Date	2022-02-10
Access Restriction	Open
Subject Keyword	Aerospace Aerospace Engineering Blended Wing–body Aerodynamics Computational Fluid Dynamics
Content Type	Text
Resource Type	Article

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