A new vortex generator model for use in complex configuration CFD solvers

May, Nicholas E.

doi:10.2514/6.2001-2434

Cited by 20 publications

(7 citation statements)

References 6 publications

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“…The use of k-! turbulence modeling in S-shape diffusers with vortex separation and compressible flow in transonic diffusers is also supported by other researchers ( [22][23][24]). The turbulence intensity and viscosity rate were set as 1% and 10, respectively, for the freestream turbulence level.…”

supporting

confidence: 49%

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

Jin¹,

Taghavi²,

Farokhi

2011

International Journal of Turbo and Jet Engines

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Abstract. The effect of flow angularity on an S-duct inlet with icing is computationally investigated. Flow angularity is simulated through angle-of-attack, and sideslip in addition to asymmetrical ice accretion on the inlet lip. A commercial CFD code, STAR-CCM+ is used for the steadystate computations with the shear-stress transport (SST) k-! turbulence model. Symmetrical and asymmetrical glaze ice shapes are computationally simulated on the inlet lip. The symmetrical glaze ice uniformly covers the entire cowl lip; whereas the asymmetrical glaze ice is simulated on a 1=4 sector of the inlet lip and is positioned on top, bottom or side of the inlet lip. The results indicate that flow angularity, whether in angle-of-attack or sideslip, aggravates the low performance of inlets with icing. The total pressure recovery suffers an additional 2% loss and the inlet mass flow rate drops by 7% when the inlet is at C20 ı angle of attack, as compared to zero angle, for flight Mach number of 0.34. The extent of loss in total pressure and a drop in mass flow rate depends on the asymmetrical icing location as well as the inlet angle-of-attack and sideslip. In addition, the ice-induced flow blockage is identified as a critical inlet performance parameter, since the symmetrical (360 ı ) glaze ice with its wider flow blockage creates a lower total pressure recovery than the asymmetrical (90 ı ) glaze ice at all angles of attack or sideslip.

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supporting

confidence: 49%

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

Jin¹,

Taghavi²,

Farokhi

2011

International Journal of Turbo and Jet Engines

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“…This is a simplified version of the vortex system generated close to the wing tips, but the reader is reminded that the Augmented Betz method is also capable of producing more complex, multivortex systems. The methodology of generating this system is similar to "effect-based" models used in Gawande, Dhoble, and Zodpe [2014], Waithe [2004], and Lane [2001]. More complex immersed boundary-based solvers may be used in the future.…”

Section: Sos Analysis and Optimization Resultsmentioning

confidence: 99%

Application of Multidisciplinary Systems‐of‐Systems Optimization to an Aircraft Design Problem

Subramanian

DeLaurentis

2016

Systems Engineering

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A generic mathematical formulation for Systems‐of‐Systems (SoS) optimization problems is presented. SoS optimization problems resemble the structure of a tree of Multidisciplinary Design Optimization (MDO) problems with additional unique features. The framework for solving such problems involves features from evolutionary computing, platform‐based design, and evolving design spaces. One important aspect of SoS Engineering, often overlooked, is the role it plays in improving the design of individual systems. In this vein, this work has sought to exemplify such a synergistic approach for aircraft design. A large‐scale SoS optimization problem for designing noise‐optimal aircraft and improved procedures for the approach phase is studied. Modules involving Computational Fluid Dynamics (CFD), noise modeling, multifidelity analysis, topology optimization, and autotuned control systems are used to obtain optimal solutions.

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“…A few approaches to the design of such a body force are available in the literature (see, e.g., [18][19][20][21][22][23]). In this study, we use a simple approach that is based on the direct numerical simulation study of Liu et al [23] and was shown to be robust and quite accurate within SARC SRANS computations in [24].…”

Section: Representation Of Vortex Generators By a Body Forcementioning

confidence: 99%

Evaluation of Vortex Generators for Separation Control in a Transcritical Cylinder Flow

et al. 2015

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A numerical study is presented, aimed at evaluating the capability of vortex generators to produce a significant delay of separation and drag reduction in flows past smooth bluff bodies in the transcritical flow regime, with turbulent boundary layers ahead of separation. A fairly large series of steady Reynolds-averaged Navier-Stokes computations is carried out of the incompressible flow past a circular cylinder, with a simple and generic geometry, with and without vortex generators. Their effect is emulated with a body force, applied in a refined-grid region, instead of gridding the actual geometry. The flow is treated as steady, for reasons that are discussed. The parametric study includes 10 different vortex generator designs, as well as varying positions, spacings, and heights. Drag reductions of up to 60% are obtained, including those with sub-boundary-layer designs, with a height equal to half the boundary-layer thickness. Design recommendations are given, with the tolerance to vortex shedding and other variations in the flow conditions taken into account. Nomenclature= components of body-force-emulating vortex generators in local coordinate system g 0x , g 0 y , g 0 z = functions controlling spatial variation of body-force components h = height of vortex generator k = turbulent kinetic energy L z = distance between vortex generators in array U, V, W = velocity components in global coordinate system fx; y; zg u, v, w = velocity components in local coordinate system fx 0 ; y 0 ; z 0 g α = polar angle of a point on cylinder surface (zero at forward stagnation point) β = angle of attack Γ = circulation Δ = half-width of vortex generator ν = molecular viscosity ν t = eddy viscosity τ xy = shear stress ω = specific dissipation rate of turbulent kinetic energy Subscripts w = parameters on cylinder wall 0 = parameters at vortex generator location ∞ = freestream parameters

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A new vortex generator model for use in complex configuration CFD solvers

Cited by 20 publications

References 6 publications

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

Application of Multidisciplinary Systems‐of‐Systems Optimization to an Aircraft Design Problem

Evaluation of Vortex Generators for Separation Control in a Transcritical Cylinder Flow

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