CFD Predictions for Transonic Performance of the ERA Hybrid Wing-Body Configuration (Invited)

Deere, Karen A.; Luckring, James M.; McMillin, S. Naomi; Flamm, Jeffrey D.; Roman, Dino

doi:10.2514/6.2016-0266

Cited by 5 publications

(5 citation statements)

References 6 publications

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“…Optimization runs for a minimum drag objective showed the major impact over the design of pressure drag. Deere et al [13] focused on the aerodynamic predictions of a Hybrid Wing-Body (HWB) to simulate transonic cruise condition. Three different configurations of the same BWB were considered in order to evaluate the influence of engines over global aerodynamic prediction: (i) complete aircraft configuration; (ii) the wing-body tail configuration; (iii) and the isolated nacelle configuration.…”

Section: Related Workmentioning

confidence: 99%

“…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. 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].…”

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: Related Workmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

et al. 2022

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“…Prior to the current study, both USM3D/SA and OVERFLOW/SA had been used extensively in the ERA HWB project, and the codes had correlated well with each other in many applications. 10…”

Section: Flow Solversmentioning

confidence: 99%

An Application of CFD to Guide Forced Boundary-Layer Transition for Low-Speed Tests of a Hybrid Wing-Body Configuration

Luckring

Deere

Childs

et al. 2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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A hybrid transition trip-dot sizing and placement test technique was developed in support of recent experimental research on a hybrid wing-body configuration under study for the NASA Environmentally Responsible Aviation project. The approach combines traditional methods with Computational Fluid Dynamics. The application had threedimensional boundary layers that were simulated with either fully turbulent or transitional flow models using established Reynolds-Averaged Navier-Stokes methods. Trip strip effectiveness was verified experimentally using infrared thermography during a low-speed wind tunnel test. Although the work was performed on one specific configuration, the process was based on fundamental flow physics and could be applicable to other configurations. Nomenclature Av data average over an interval s distance along a surface b 1b 3 spanwise coordinate for leading-edge sweep break U ∞ free-stream reference velocity C f skin friction coefficient x, y, z body-axis Cartesian coordinates C p pressure coefficient u, v, w Cartesian velocity components c wing chord c ref reference chord  angle of attack, deg. H 12 boundary-layer shape factor,     boundary layer thickness k roughness height    boundary layer displacement thickness M Mach number  boundary layer momentum thickness Ra data range (maximum-minimum) over an interval  leading-edge sweep angle, deg. Re cref reference chord Reynolds number, U ∞ c ref /   viscosity Re k roughness height Reynolds number, u k k /  k  kinematic viscosity,  Re x length Reynolds number, U ∞ x /   density Re  momentum thickness Reynolds number, U e  /   Subscripts e value at edge of boundary layer ∞ free-stream reference conditions k value at roughness height

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“…The research of the engine influences on conventional transport aerodynamic by using FTN/WPN models has been going for decades now (Lange, 1986;Stankowski et al, 2017), but the corresponding research on BWB only emerged in the last few years. Recently, Boeing/NASA in its Environmentally Responsible Aviation (ERA) project has performed a series of research on the Ultra-High Bypass integration of HWB (Hybrid Wing Body, also referred to as the BWB) using both FTN/WPN models (Deere, Luckring, McMillin, Flamm, & Roman, 2016;Flamm, James, & Bonet, 2016;Schuh et al, 2016). BWB300 is a 300-passenger BWB civil aircraft.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation for the differences between FTN/WPN engine models aerodynamic influence on BWB300 airframe

Zhang

2020

Engineering Applications of Computational Fluid Mechanics

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The difference of the aerodynamic influence of two engine models -the Flow Through Nacelle (FTN) and With Powered Nacelle (WPN) -on BWB300 airframe is analyzed by using the 3-D unsteady compressible Reynolds-Averaged Navier-Stokes (RANS) computation. The results indicate that at cruise condition, the engine shape is a primary factor affecting the BWB airframe upper fuselage surface flow, the two engine models exhibit a similar aerodynamic influence on the BWB airframe. However, at takeoff condition, the two engine models' aerodynamic influence on the airframe is different, because of the air suction caused by the WPN engine model affecting the airframe upper fuselage surface flow obviously. Moreover, at both cruise and takeoff conditions, the tube formed by the engine and airframe shape changes the surface flow under the engine and the air suction caused by the engine power accelerates the surface flow near the engine. ARTICLE HISTORY

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CFD Predictions for Transonic Performance of the ERA Hybrid Wing-Body Configuration (Invited)

Cited by 5 publications

References 6 publications

Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

An Application of CFD to Guide Forced Boundary-Layer Transition for Low-Speed Tests of a Hybrid Wing-Body Configuration

Numerical simulation for the differences between FTN/WPN engine models aerodynamic influence on BWB300 airframe

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