Low-speed Aerodynamic Investigations of a Hybrid Wing Body Configuration

Vicroy, Dan D.; Gatlin, Gregory M.; Jenkins, Luther N.; Murphy, Patrick C.; Carter, Melissa B.

doi:10.2514/6.2014-2563

Cited by 6 publications

(7 citation statements)

References 18 publications

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“…The trend of aerodynamic coefficients related to flight attitudes is shown in Table 1, discussed considering the flow behaviour on the leeward surface. Results are compared to low-subsonic numerical and experimental data collected for the N2A aeroshape, as hereinafter discussed [6,[14][15][16]. To further support comparisons with experimental data, streamlines and skin-friction lines over BWB at different AoAs are also provided.…”

Section: Results Discussion With Experimental Data Comparisonsmentioning

confidence: 99%

“…Additionally, WT experimental test campaigns are also available for the N2A aeroshape. They have provided a comprehensive dataset of the low speed aerodynamic performance of this aircraft [14][15][16].…”

Section: Related Workmentioning

confidence: 99%

“…This aeroshape was derived by a NASA Research Announcement (NRA) aimed at developing an efficient low-noise HWB subsonic transport aircraft [18]. NRA was also aimed to meet the goals of both fuel and noise reductions, and additionally to study the subsonic aerodynamics performance of the HBW configuration [14][15][16].…”

Section: Aircraft Aeroshape and Aerodynamicsmentioning

confidence: 99%

“…Moreover, according to Ref. [16], there are two WT tests, namely T597 conducted with a closed test section and T612, which refers to measurements conducted with an open test section. Some data of both these tests are considered hereinafter for the assessment of the reliability of the present numerical research effort.…”

Section: Cfd Test Matrixmentioning

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: Results Discussion With Experimental Data Comparisonsmentioning

confidence: 99%

Section: Related Workmentioning

confidence: 99%

Section: Aircraft Aeroshape and Aerodynamicsmentioning

confidence: 99%

Section: Cfd Test Matrixmentioning

confidence: 99%

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Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

et al. 2022

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“…An additional study including comparisons of wind tunnel and water tunnel results is provided in Ref. 17.…”

Section: Introductionmentioning

confidence: 99%

Hybrid Wing Body Model Identification Using Forced-Oscillation Water Tunnel Data

Murphy

Vicroy

Kramer

et al. 2014

AIAA Atmospheric Flight Mechanics Conference

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Static and dynamic testing of the NASA 0.7 percent scale Hybrid Wing Body (HWB) configuration was conducted in the Rolling Hills Research Corporation water tunnel to investigate aerodynamic behavior over a large range of angle-of-attack and to develop models that can predict aircraft response in nonlinear unsteady flight regimes. This paper reports primarily on the longitudinal axis results. Flow visualization tests were also performed. These tests provide additional static data and new dynamic data that complement tests conducted at NASA Langley 14-by 22-Foot Subsonic Tunnel. HWB was developed to support the NASA Environmentally Responsible Aviation Project goals of lower noise, emissions, and fuel burn. This study also supports the NASA Aviation Safety Program efforts to model and control advanced transport configurations in loss-of-control conditions. SubscriptsA = amplitude a = aero forces and moments: N, Y, l, m, or n E = measured value Superscripts ^ = estimated value ~ = mean value A j , B j = Fourier coefficients a, b 1 = deficiency function parameters b = wing span, ft C N , C Y = normal and side force coefficients C l , C n = rolling and yawing-moment coefficients C m = pitching-moment coefficients c = mean aerodynamic chord, ft a F α , a F β = deficiency functions f = frequency, Hz k = reduced f, / bf V π , or / cf V π m = no. of harmonics in Fourier expansion N = number of data points p, q, r = roll, pitch, and yaw rates, rad/sec R 2 = coefficient of determination S = reference area, ft 2 T = dimensional time constant, sec t = time, sec V = velocity, fps α = angle-of-attack, rad or deg α 0 = initial angle-of-attack in forced oscillation experiments, rad or deg β = sideslip angle, rad or deg η = state variable σ = standard error τ = dummy integration variable τ 1 = non-dimensional time constant, 1 1 2V b b       ω = angular frequency, rad/sec a C γ = in-phase coefficients, γ = α or β a C ζ = out-of-phase coefficients, ζ = p, q, or r , E r SS SS = residual and total sum of squares American Institute of Aeronautics and Astronautics 1 Downloaded by NANYANG TECHNICAL UNIVERSITY on October 1, 2015 | http://arc.aiaa.org |

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