Load Control of Natural-Laminar-Flow Wing via Boundary Layer Control

Stalewski, W.; Sznajder, Janusz

doi:10.7712/100016.2271.15624

Cited by 4 publications

(3 citation statements)

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“…The shock wave boundary layer interaction on V2C airfoil was investigated experimentally by Placek et al (2016) and Stryczniewicz et al (2016). Reduction of shock wave oscillations by means of smart micro vanes was described by Stalewski and Sznajder (2016). In this paper, implementation of RVGs to reduce shock wave oscillations and improve lift-to-drag ratio is presented, together with the modified BAY model effect.…”

Section: Resultsmentioning

confidence: 96%

Source term model for rod vortex generator

Kwiatkowski

Flaszyński

Żółtak

2019

AEAT

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Purpose The simulations of grid-resolved rod vortex generators (RVGs) require high computational cost and time. Additionally, the computational mesh topology must be adjusted to rods geometries. The purpose of this study is to propose the new source term model for RVG. Design/methodology/approach The model was proposed by modification of Bender, Anderson, Yagle (BAY) model used to predict flows around different type of vortex generators (VGs) – vanes. Original BAY model was built on lifting line theory. The proposed model was implemented in ANSYS Fluent by means of the user-defined function technique. Additional momentum and energy sources are imposed to transport equations. Findings The computational results of source term model were validated against experimental data and numerical simulation results for grid-resolved rod. It was shown that modified BAY model can be successfully used for RVG in complex cases. An example of BAY model application for RVG on transonic V2C airfoil with strongly oscillating shock waves is presented. Aerodynamic performance predicted numerically by means of both approaches (grid resolved RVG and modeled) is in good agreement, what indicates application opportunity of the proposed model to complex cases. Practical implications Modified BAY model can be used to simulate the influence of RVGs in complex real cases. It allows for time/cost reduction if the location or distribution of RVG has to be optimized on a profile, wing or in the channel. Originality/value In the paper, the new modification of BAY model was proposed to simulate RVGs. The presented results are innovative because of original approach to model RVGs.

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Section: Resultsmentioning

confidence: 96%

Source term model for rod vortex generator

Kwiatkowski

Flaszyński

Żółtak

2019

AEAT

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“…12 shows that for high Mach numbers in transonic flow, around Ma = 0.70 differences in L/D ratio between the investigated configurations are much lower than at low Mach numbers and reduction of L/D due to turbulisation with respect to clean airfoil is about 2.25% and this loss is weakly dependent on chordwise position of turbulators. This effect is due to interactions of compression waves produced by the turbulator with main shockwave, reducing wave drag, which is described in more detail in [4]. This feature makes the turbulator worth to consider as a retractable device, stowed in steady-flow conditions and deployed close to buffet boundary.…”

Section: Comparison Of Lift-to-drag Ratio For Clean Airfoil and Formentioning

confidence: 99%

Analysis of Effects of Shape and Location of Micro-Turbulators on Unsteady Shockwave-Boundary Layer Interactions in Transonic Flow

Sznajder¹,

Kwiatkowski²

2016

Journal of KONES. Powertrain and Transport

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Solutions for turbulisation of a part of laminar boundary layer upstream of shockwave on laminar airfoil in transonic flow were investigated by means of solution of Unsteady Reynolds-Averagd Navier-Stokes equations using as a closure the four-variable Transition SST turbulence model of ANSYS FLUENT solver. This turbulence model has the capability of resolving laminar-turbulent transition occurring in undisturbed flow as well as under the influence of flow-control devices. The aim of the work was to investigate possibilities of improvement of aerodynamic characteristics of laminar wing of a prospective transport aircraft in adverse conditions characterised by occurrence of a shockwave over a laminar-turbulent transition region with separation of laminar flow under the shockwave. The subject is important for application of laminar flow technology, offering economic and environmental advantages due to decreased friction drag, into civil transport aviation. Natural laminar-turbulent transition in the investigated conditions takes place with occurrence of "laminar separation bubble" under the foot of a shockwave and the resulting shockwave is intensive and prone to unsteady oscillations, the "buffet" phenomenon, limiting operational range of flight parameters. In order to counteract the harmful effects of natural laminar-turbulent transition in transonic flow two types of turbulators, placed upstream of the shockwave, were investigated. One of them consisted of delta-shaped vortex generators, producing chordwise-oriented vortices. The other consisted of rectangular micro-vanes, perpendicular to flow and to airfoil surface producing vortices of rotation axes oriented spanwise. Effectiveness of both types of turbulators was investigated for varying height and their location on airfoil chord. Both types of turbulators have proved their effectiveness in tripping laminar boundary layer. The specific effects of the tutbulators, different for each type occurred in the region where laminar separation takes place on clean airfoil. As a result, the changes of lift and drag were different for each type of turbulators.

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“…Therefore, not all methods of the separated flow control developed for transonic turbulent aerofoils 8 can be suitable for laminar aerofoils. In Stalewski and Sznajder, 9 it was proposed to use a turbulator of special type to improve the resistance of the aerofoil to laminar transonic buffet. The numerical simulations confirm the possibility of suppressing the buffet, but at the same time the lifting performance of the aerofoil decreases.…”

Section: Introductionmentioning

confidence: 99%

Effective plasma buffet and drag control for laminar transonic aerofoil

Polivanov

Sidorenko

Маслов

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The effect of plasma actuators on shock wave–laminar boundary layer interaction was studied experimentally on transonic laminar aerofoil. The unsteady characteristics of the separation zone including the transonic buffet were measured. Two kinds of electrical discharge actuators were used for the flow control. Successful suppression of separated flow and laminar transonic buffet by plasma actuators was demonstrated. An analysis of the effect of power and frequency of the discharge on shock wave–laminar boundary layer interaction was carried out. High efficiency ratio of the separation control by plasma actuators was achieved in the experiments.

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Load Control of Natural-Laminar-Flow Wing via Boundary Layer Control

Abstract: Abstract. The concept of Smart Micro Vanes (SMV) has been developed and investigated

Cited by 4 publications

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Source term model for rod vortex generator

Source term model for rod vortex generator

Analysis of Effects of Shape and Location of Micro-Turbulators on Unsteady Shockwave-Boundary Layer Interactions in Transonic Flow

Effective plasma buffet and drag control for laminar transonic aerofoil

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