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Dr. Hossein Zare-Behtash
Aerospace Sciences Division, School of Engineering, University of Glasgow, Glasgow G12 8QQ, Scotland, UK

Basic Info


Research Keywords & Expertise

0 Wind Tunnel Testing
0 Unsteady Aerodynamics
0 Shock Physics
0 Fluid–thermal–structure interactions
0 Nanophotonic fluid sensor, flow control

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Energy deposition
Wind Tunnel Testing
Advanced flow diagnostics
Shock–vortex interactions

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Journal article
Published: 01 January 2021 in Geosciences
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Research into the geometric nests built by white-spotted pufferfish indicated the nest’s potential for flow control and reduction in flow velocity. However, studies to date have only focused on the construction process and behaviour of the male pufferfish. Hence, the form and functions of the unique features of the nest remain unclear. The present study aims to explore the flow features most useful in understanding the habitat conditions of the nest through a combination of photogrammetric reconstructions of the nest features and two-dimensional (2D) computational fluid dynamic simulations. The findings show the role of the nest structure in reducing the flow velocity and shear stress within the nesting site. Analysis of shear stress indicates that male pufferfish build the outer zones of the nest with coarser material that improves the overall shear strength of these areas. The study identified the function of the nest structure in the protection of the eggs through reduction in flow variations and improved aeration. The addition of shell fragments to the nest peaks by the male pufferfish contributes to the resiliency of the nest structure and ensures a stable bed surface at the central zone.

ACS Style

Abdulla Shameem; Manousos Valyrakis; Hossein Zare-Behtash. A Fluid Dynamics Approach for Assessing the Intelligent Geomorphic Design of the Japanese Pufferfish Nest. Geosciences 2021, 11, 22 .

AMA Style

Abdulla Shameem, Manousos Valyrakis, Hossein Zare-Behtash. A Fluid Dynamics Approach for Assessing the Intelligent Geomorphic Design of the Japanese Pufferfish Nest. Geosciences. 2021; 11 (1):22.

Chicago/Turabian Style

Abdulla Shameem; Manousos Valyrakis; Hossein Zare-Behtash. 2021. "A Fluid Dynamics Approach for Assessing the Intelligent Geomorphic Design of the Japanese Pufferfish Nest." Geosciences 11, no. 1: 22.

Journal article
Published: 09 December 2020 in Vibration
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A complex fluid-structure interaction can often create nonlinear dynamic behaviour in the structure. This can be better estimated using nonlinear modal analysis, capable of identifying and quantifying the nonlinearity in the structure. In this study, the case of a vibrating beam submerged in liquid using a nonlinear parameter identification method is presented. This system is considered as an alternative propulsion mechanism, hence understanding the interaction between the fluid and the structure is necessary for its control. Here, impulse signals are used to characterise the numerical and experimental dynamics response of the system. Since the transient responses contain of a multi-component vibratory signals, a vibration decomposition method is used to separate the time response signals based on the dominant amplitude in the frequency response function. The separated time-series signals are then fitted to the nonlinear identification method to construct the backbone and damping curves. The modal parameters obtained from experimental data are then used as a base for the development of the analytical models. The analytical approaches are based on the Euler-Bernoulli beam theory with additional mass and quadratic damping functions to account for the presence of the fluid. Validations are carried out by comparing the dynamic responses of the analytical and experimental measurements demonstrating the accuracy of the model and hence, its suitability for control purposes.

ACS Style

Skriptyan N. H. Syuhri; Hossein Zare-Behtash; Andrea Cammarano. Investigating the Influence of Fluid-Structure Interactions on Nonlinear System Identification. Vibration 2020, 3, 521 -544.

AMA Style

Skriptyan N. H. Syuhri, Hossein Zare-Behtash, Andrea Cammarano. Investigating the Influence of Fluid-Structure Interactions on Nonlinear System Identification. Vibration. 2020; 3 (4):521-544.

Chicago/Turabian Style

Skriptyan N. H. Syuhri; Hossein Zare-Behtash; Andrea Cammarano. 2020. "Investigating the Influence of Fluid-Structure Interactions on Nonlinear System Identification." Vibration 3, no. 4: 521-544.

Accepted manuscript
Published: 18 November 2020 in Journal of Experimental Botany
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Plants are known to exhibit a thigmomorphogenetic response to mechanical stimuli by altering their morphology and mechanical properties. Wind is widely perceived as mechanical stress and in many experiments its influence is simulated by applying mechanical perturbations. However, it is known that wind-induced effects on plants can differ and at times occur even in the opposite direction compared with those induced by mechanical perturbations. In the present study, the long-term response of Arabidopsis thaliana to a constant unidirectional wind was investigated. We found that exposure to wind resulted in a positive anemotropic response and in significant alterations to Arabidopsis morphology, mechanical properties, and anatomical tissue organization that were associated with the plant’s strategy of acclimation to a windy environment. Overall, the observed response of Arabidopsis to wind differs significantly from previously reported responses of Arabidopsis to mechanical perturbations. The presented results suggest that the response of Arabidopsis is sensitive to the type of mechanical stimulus applied, and that it is not always straightforward to simulate one type of perturbation by another.

ACS Style

Oleksandr Zhdanov; Michael R Blatt; Hossein Zare-Behtash; Angela Busse. Wind-evoked anemotropism affects the morphology and mechanical properties of Arabidopsis. Journal of Experimental Botany 2020, 72, 1906 -1918.

AMA Style

Oleksandr Zhdanov, Michael R Blatt, Hossein Zare-Behtash, Angela Busse. Wind-evoked anemotropism affects the morphology and mechanical properties of Arabidopsis. Journal of Experimental Botany. 2020; 72 (5):1906-1918.

Chicago/Turabian Style

Oleksandr Zhdanov; Michael R Blatt; Hossein Zare-Behtash; Angela Busse. 2020. "Wind-evoked anemotropism affects the morphology and mechanical properties of Arabidopsis." Journal of Experimental Botany 72, no. 5: 1906-1918.

Journal article
Published: 01 September 2020 in Physics of Fluids
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Wingtip vortices are an important phenomenon in fluid dynamics due to their complex and negative impacts. Despite numerous studies, the current understanding of the inner vortex is very limited; thus, a basis for the design of effective wingtip geometry and vortex manipulation is narrow. This work examines the structure of the trailing vortex shed from a swept-tapered wing, analogous to a commercial aircraft topology. Stereoscopic particle imaging velocimetry has been utilized to compare the vortex structure and development through several angles of attack at various downstream stations for a fixed Reynolds number (Re = 1.5 × 106). After correcting for vortex meander through helicity-based spatial localization of the vortex core, relationships between the vortex core velocity/vorticity fields, core shape, and turbulent properties have been examined. Subsequently, the vortex is found to exhibit a layered structure with slow linear rates of dissipation indicative of laminar diffusion mechanisms, despite being a turbulent vortex. The turbulent kinetic energy distribution in the vortex signals that relaminarization of the inner core occurs. Consideration of the streamline curvature around the core, via examination of the local Richardson number, indicated that a laminar core structure had formed within which large-scale turbulent eddies could not contribute to the turbulent diffusion of vorticity away from the core. The normalized circulation within the vortex core has been shown to exhibit self-similar behavior typical of the fully developed axisymmetric vortices.

ACS Style

S. N. Skinner; R. B. Green; H. Zare-Behtash. Wingtip vortex structure in the near-field of swept-tapered wings. Physics of Fluids 2020, 32, 095102 .

AMA Style

S. N. Skinner, R. B. Green, H. Zare-Behtash. Wingtip vortex structure in the near-field of swept-tapered wings. Physics of Fluids. 2020; 32 (9):095102.

Chicago/Turabian Style

S. N. Skinner; R. B. Green; H. Zare-Behtash. 2020. "Wingtip vortex structure in the near-field of swept-tapered wings." Physics of Fluids 32, no. 9: 095102.

Research article
Published: 22 May 2019 in ACS Applied Nano Materials
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The two complementary technologies of colloidal upconverting nano-emitters and maskless photolithography are exploited to fabricate nano-engineered optically-active surfaces for anti-counterfeiting applications based on multiphoton absorption phenomenon in lanthanide nanocomposites with a visualization wavelength in the NIR. It is demonstrated that the unique optical, thermal, and temporal characteristics of these versatile upconverting surface distinguishes them from their counterparts. A unique behaviour that is captured is the ability to actively tune their emission color by modifying the pumping power, temperature, and excitation frequency. A new low-cost negative photoresist is employed for implementation of maskless photolithography of single and double-color labels using two efficient upconverting nanocomposites based on NaYF4:Yb3+,Er3+ and NaYF4:Yb3+,Tm3+ nano-emitters. What’s more, it is shown that the detectability of the proposed anti-counterfeiting approach can be carried out using just a smartphone. Each of the emission peaks of the upconversion nanoparticles is associated with a different multiphoton absorption mechanism and their thermosensitivity varies from one peak to another. Furthermore, their photoluminescent color changes by scanning the excitation beam impinging on the surfaces comprised of both upconversion nanoparticles doped in the UV-curable resist. Longterm photostability of these surfaces under continuous excitation by a high power laser makes them a promising nano-emitters for the next generation of anti-counterfeiting labels.

ACS Style

Fatemeh Kaboli; Nahid Ghazyani; Mohammadreza Riahi; Hossein Zare-Behtash; Mohammad Hossein Majles Ara; Esmaeil Heydari. Upconverting Nanoengineered Surfaces: Maskless Photolithography for Security Applications. ACS Applied Nano Materials 2019, 2, 3590 -3596.

AMA Style

Fatemeh Kaboli, Nahid Ghazyani, Mohammadreza Riahi, Hossein Zare-Behtash, Mohammad Hossein Majles Ara, Esmaeil Heydari. Upconverting Nanoengineered Surfaces: Maskless Photolithography for Security Applications. ACS Applied Nano Materials. 2019; 2 (6):3590-3596.

Chicago/Turabian Style

Fatemeh Kaboli; Nahid Ghazyani; Mohammadreza Riahi; Hossein Zare-Behtash; Mohammad Hossein Majles Ara; Esmaeil Heydari. 2019. "Upconverting Nanoengineered Surfaces: Maskless Photolithography for Security Applications." ACS Applied Nano Materials 2, no. 6: 3590-3596.

Preprint content
Published: 07 February 2019
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Animal migration is highly sensitised to environmental and biological cues, yet plant dispersal is considered largely passive. The common dandelion, Taraxacum officinale, is a classic example of a wind-dispersed plant and has an intricate haired pappus facilitating flight. This pappus facilitates enables the formation of a separated vortex ring (SVR) during flight (1); however, the pappus structure is not static but reversibly changes shape by closing in response to moisture. Here we characterise the biomechanical function of the pappus morphing regarding SVR dynamics and flight capacity. When the pappus closes, the falling velocity is greatly increased and the velocity deficit within the vortex decreased. To understand the implications of this structural-functional change, we used historic meteorological data to simulate dispersal distance. Dispersal distances were reduced with the pappus closed, and so was detachment. We propose that moisture-dependent pappus-morphing serves to retain seeds in favourable moist niches, providing a form of informed dispersal (2) that has not been characterised in plants on such a short-term, responsive time scale (3).

ACS Style

Madeleine Seale; Oleksandr Zhdanov; Cathal Cummins; Erika Kroll; Michael R Blatt; Hossein Zare-Behtash; Angela Busse; Enrico Mastropaolo; Ignazio Maria Viola; Naomi Nakayama. Informed dispersal of the dandelion. 2019, 542696 .

AMA Style

Madeleine Seale, Oleksandr Zhdanov, Cathal Cummins, Erika Kroll, Michael R Blatt, Hossein Zare-Behtash, Angela Busse, Enrico Mastropaolo, Ignazio Maria Viola, Naomi Nakayama. Informed dispersal of the dandelion. . 2019; ():542696.

Chicago/Turabian Style

Madeleine Seale; Oleksandr Zhdanov; Cathal Cummins; Erika Kroll; Michael R Blatt; Hossein Zare-Behtash; Angela Busse; Enrico Mastropaolo; Ignazio Maria Viola; Naomi Nakayama. 2019. "Informed dispersal of the dandelion." , no. : 542696.

Journal article
Published: 21 November 2018 in Physics of Fluids
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The thermal perturbation caused by a nanosecond pulsed dielectric barrier discharge (ns-DBD) plasma actuator may lead to boundary layer transition. Hence, understanding of the thermal flow induced by the ns-DBD plasma actuator will contribute to the development of an efficient flow control device for various engineering applications. In this study, the spatial density distribution related to the thermal flow was experimentally investigated using both qualitative and quantitative schlieren techniques. The focus of this study is to understand the initial temporal variation of the spatial density distribution above the ns-DBD plasma actuator in quiescent air. The quantitative visualisation showed that a hot plume is generated from the edge of the exposed electrode and moves slightly towards the ground electrode. A possible explanation is that an ionic wind and/or an induced jet leads to the movement of the hot plume. However, the plasma-induced flow (the ionic wind and the induced jet) is generated after the...

ACS Style

Takahiro Ukai; Andrew Russell; Hossein Zare-Behtash; Konstantinos Kontis. Temporal variation of the spatial density distribution above a nanosecond pulsed dielectric barrier discharge plasma actuator in quiescent air. Physics of Fluids 2018, 30, 116106 .

AMA Style

Takahiro Ukai, Andrew Russell, Hossein Zare-Behtash, Konstantinos Kontis. Temporal variation of the spatial density distribution above a nanosecond pulsed dielectric barrier discharge plasma actuator in quiescent air. Physics of Fluids. 2018; 30 (11):116106.

Chicago/Turabian Style

Takahiro Ukai; Andrew Russell; Hossein Zare-Behtash; Konstantinos Kontis. 2018. "Temporal variation of the spatial density distribution above a nanosecond pulsed dielectric barrier discharge plasma actuator in quiescent air." Physics of Fluids 30, no. 11: 116106.

Journal article
Published: 15 August 2018 in European Journal of Mechanics - B/Fluids
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The understanding of the formation of shock trains in high-speed engines is vital for the improvement of engine design. The formation of these flow structures in a narrow duct, driven by the presence of the viscous effects on the walls, is an extremely complex process that is not fully understood. This investigation demonstrates the high sensitivity of the shock train to the solving equations. The establishment of the shock train in the duct mainly depends on the way that the boundary layer develops on the walls. The k-ω Wilcox model confirms to be the most suitable to accurately reproduce the subtle features close to the solid boundary. The assumption of two-dimensional flow is not completely accurate for describing internal flows where the three-dimensional effects from the shock wave/boundary layer interactions cannot be neglected. The centreline flow properties show that the first shock wave has the same strength in the two- and three-dimensional cases. However, in the three-dimensional case the thinner boundary layer behind the leading shock allows the flow to expand more in the subsonic region causing a stronger deceleration of the flow behind the first shock.

ACS Style

F. Gnani; H. Zare-Behtash; C. White; K. Kontis. Numerical investigation on three-dimensional shock train structures in rectangular isolators. European Journal of Mechanics - B/Fluids 2018, 72, 586 -593.

AMA Style

F. Gnani, H. Zare-Behtash, C. White, K. Kontis. Numerical investigation on three-dimensional shock train structures in rectangular isolators. European Journal of Mechanics - B/Fluids. 2018; 72 ():586-593.

Chicago/Turabian Style

F. Gnani; H. Zare-Behtash; C. White; K. Kontis. 2018. "Numerical investigation on three-dimensional shock train structures in rectangular isolators." European Journal of Mechanics - B/Fluids 72, no. : 586-593.

Journal article
Published: 01 April 2018 in Journal of Fluids and Structures
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Non-planar wing configurations are often hypothesised as a means for improving the aerodynamic efficiency of large transport aircraft; C-wings may have the ability to exploit and unify drag reduction, aeroelasticity, and dynamics and control but their capacity to do so is ambiguous. The purpose of this work is to provide an experimental demonstration with the aim of verifying the C-wing configurations practical application. Thus, the main objective of this investigation is to quantify the C-wing’s ability for drag and load alleviation relative to a planar wing of equivalent wingspan, lift, and root bending moment at Re=1.5×106Re=1.5×106. Surface clay flow visualisations have been used to provide insight into the flow over the wing surface. Aerodynamic performance metrics show that despite the C-wing operating with a 19.1%19.1% higher wing wetted area, a peak total drag reduction of 9.5%9.5% at α=6°α=6° is achieved in addition to a 1.1%1.1% reduction in the wing root bending moment for equivalent lift. Force platform measurements in combination with laser vibrometry enabled a detailed understanding of the vibrational characteristics between the model and the wind tunnel. It is shown that the C-wing can passively attenuate buffet induced vibrations of the main-wing by up to 68.6%68.6% whilst simultaneously reducing total drag without a significant increase in wing weight or root bending moment.

ACS Style

Shaun Skinner; Hossein Zare-Behtash. Study of a C-wing configuration for passive drag and load alleviation. Journal of Fluids and Structures 2018, 78, 175 -196.

AMA Style

Shaun Skinner, Hossein Zare-Behtash. Study of a C-wing configuration for passive drag and load alleviation. Journal of Fluids and Structures. 2018; 78 ():175-196.

Chicago/Turabian Style

Shaun Skinner; Hossein Zare-Behtash. 2018. "Study of a C-wing configuration for passive drag and load alleviation." Journal of Fluids and Structures 78, no. : 175-196.

Journal article
Published: 01 April 2018 in Acta Astronautica
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The deceleration of a supersonic flow to the subsonic regime inside a high-speed engine occurs through a series of shock waves, known as a shock train. The generation of such a flow structure is due to the interaction between the shock waves and the boundary layer inside a long and narrow duct. The understanding of the physics governing the shock train is vital for the improvement of the design of high-speed engines and the development of flow control strategies. The present paper analyses the sensitivity of the shock train configuration to a back-pressure variation. The complex characteristics of the shock train at an inflow Mach number M = 2 in a channel of constant height are investigated with two-dimensional RANS equations closed by the Wilcox k-ω turbulence model. Under a sinusoidal back-pressure variation, the simulated results indicate that the shock train executes a motion around its mean position that deviates from a perfect sinusoidal profile with variation in oscillation amplitude, frequency, and whether the pressure is first increased or decreased.

ACS Style

F. Gnani; H. Zare-Behtash; C. White; K. Kontis. Effect of back-pressure forcing on shock train structures in rectangular channels. Acta Astronautica 2018, 145, 471 -481.

AMA Style

F. Gnani, H. Zare-Behtash, C. White, K. Kontis. Effect of back-pressure forcing on shock train structures in rectangular channels. Acta Astronautica. 2018; 145 ():471-481.

Chicago/Turabian Style

F. Gnani; H. Zare-Behtash; C. White; K. Kontis. 2018. "Effect of back-pressure forcing on shock train structures in rectangular channels." Acta Astronautica 145, no. : 471-481.

Journal article
Published: 01 January 2018 in Applied Soft Computing
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ACS Style

Shaun Skinner; H. Zare-Behtash. State-of-the-art in aerodynamic shape optimisation methods. Applied Soft Computing 2018, 62, 933 -962.

AMA Style

Shaun Skinner, H. Zare-Behtash. State-of-the-art in aerodynamic shape optimisation methods. Applied Soft Computing. 2018; 62 ():933-962.

Chicago/Turabian Style

Shaun Skinner; H. Zare-Behtash. 2018. "State-of-the-art in aerodynamic shape optimisation methods." Applied Soft Computing 62, no. : 933-962.

Journal article
Published: 01 December 2017 in Physics of Fluids
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The impurity effect of suspended liquid particles on the laser-induced gas breakdown was experimentally investigated in quiescent gas. The focus of this study is the investigation of the influence of the impurities on the shock wave structure as well as the low density distribution. A 532 nm Nd:YAG laser beam with an 188 mJ/pulse was focused on the chamber filled with suspended liquid particles 0.9 ± 0.63 μm in diameter. Several shock waves are generated by multiple gas breakdowns along the beam path in the breakdown with particles. Four types of shock wave structures can be observed: (1) the dual blast waves with a similar shock radius, (2) the dual blast waves with a large shock radius at the lower breakdown, (3) the dual blast waves with a large shock radius at the upper breakdown, and (4) the triple blast waves. The independent blast waves interact with each other and enhance the shock strength behind the shock front in the lateral direction. The triple blast waves lead to the strongest shock wave in all cases. The shock wave front that propagates toward the opposite laser focal spot impinges on one another, and thereafter a transmitted shock wave (TSW) appears. The TSW interacts with the low density core called a kernel; the kernel then longitudinally expands quickly due to a Richtmyer-Meshkov-like instability. The laser-particle interaction causes an increase in the kernel volume which is approximately five times as large as that in the gas breakdown without particles. In addition, the laser-particle interaction can improve the laser energy efficiency.

ACS Style

Takahiro Ukai; Hossein Zare-Behtash; Konstantinos Kontis. Suspended liquid particle disturbance on laser-induced blast wave and low density distribution. Physics of Fluids 2017, 29, 126104 .

AMA Style

Takahiro Ukai, Hossein Zare-Behtash, Konstantinos Kontis. Suspended liquid particle disturbance on laser-induced blast wave and low density distribution. Physics of Fluids. 2017; 29 (12):126104.

Chicago/Turabian Style

Takahiro Ukai; Hossein Zare-Behtash; Konstantinos Kontis. 2017. "Suspended liquid particle disturbance on laser-induced blast wave and low density distribution." Physics of Fluids 29, no. 12: 126104.

Research article
Published: 08 November 2017 in Experiments in Fluids
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Low-speed wind tunnel tests of a flexible wing semi-span model have been implemented in the \(9\times 7\) ft de Havilland wind tunnel at the University of Glasgow. The main objective of this investigation is to quantify the effect of removing the traditional peniche boundary layer spacer utilised in this type of testing. Removal of the peniche results in a stand-off gap between the wind tunnel wall and the model’s symmetry plane. This offers the advantage of preventing the development of a horseshoe vortex in front of the model, at the peniche/wall juncture. The formation of the horseshoe vortex is known to influence the flow structures around the entire model and thus alters the model’s aerodynamic behaviours. To determine the influence of the stand-off gap, several gap heights have been tested for a range of angles of attack at \(Re=1.5\times 10^6\), based on the wing mean aerodynamic chord (MAC). Force platform data have been used to evaluate aerodynamic coefficients, and how they vary with stand-off heights. Stereoscopic Particle Imaging Velocimetry (sPIV) was used to examine the interaction between the tunnel boundary layer and model’s respective stand-off gap. In addition, clay and tuft surface visualisation enhanced the understanding of how local flow structures over the length of the fuselage vary with stand-off height and angle of attack. The presented results show that a stand-off gap of four-to-five times the displacement thickness of the tunnel wall boundary layer is capable of achieving a flow field around the model fuselage that is representative of what would be expected for an equivalent full-span model in free-air—this cannot be achieved with the application of a peniche.

ACS Style

Shaun Skinner; H. Zare-Behtash. Semi-span wind tunnel testing without conventional peniche. Experiments in Fluids 2017, 58, 163 .

AMA Style

Shaun Skinner, H. Zare-Behtash. Semi-span wind tunnel testing without conventional peniche. Experiments in Fluids. 2017; 58 (12):163.

Chicago/Turabian Style

Shaun Skinner; H. Zare-Behtash. 2017. "Semi-span wind tunnel testing without conventional peniche." Experiments in Fluids 58, no. 12: 163.

Journal article
Published: 11 May 2017 in The Aeronautical Journal
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Cycloidal rotors are a novel form of propulsion system that can be adapted to various forms of transport such as air and marine vehicles, with a geometrical design differing significantly from the conventional screw propeller. Research on cycloidal rotor design began in the early 1930s and has developed throughout the years to the point where such devices now operate as propulsion systems for various aerospace applications such as micro air vehicles, unmanned air vehicles and compound helicopters. The majority of research conducted on the cycloidal rotor’s aerodynamic performance have not assessed mitigating the dynamic stall effect, which can have a negative impact on the rotor performance when the blades operate in the rotor retreating side. A solution has been proposed to mitigate the dynamic stall effect through employment of active, compliant leading-edge morphing. A review of the current state of the art in this area is presented. A two-dimensional, implicit unsteady numerical analysis was conducted using the commercial computational fluid dynamics software package STAR CCM+, on a two-bladed cycloidal rotor. An overset mesh technique, otherwise known as a chimera mesh, was used to apply complex transient motions to the simulations. Active, compliant leading-edge morphing is applied to an oscillating NACA 0015 aerofoil to attempt to mitigate the dynamic stall whilst maintaining the positive dynamic lift coefficient (Cl) contributions. It was verified that by applying a pulsed input leading-edge rotational morphing schedule, the leading-edge vortex does not fully form and the large flow separation is prevented. Further work in this investigation will focus on coupling the active, leading-edge motion to the cycloidal rotor model with the aim to maximise aerodynamic performance.

ACS Style

L. Ferrier; M. Vezza; H. Zare-Behtash. Improving the aerodynamic performance of a cycloidal rotor through active compliant morphing. The Aeronautical Journal 2017, 121, 901 -915.

AMA Style

L. Ferrier, M. Vezza, H. Zare-Behtash. Improving the aerodynamic performance of a cycloidal rotor through active compliant morphing. The Aeronautical Journal. 2017; 121 (1241):901-915.

Chicago/Turabian Style

L. Ferrier; M. Vezza; H. Zare-Behtash. 2017. "Improving the aerodynamic performance of a cycloidal rotor through active compliant morphing." The Aeronautical Journal 121, no. 1241: 901-915.

Journal article
Published: 01 February 2017 in Experimental Thermal and Fluid Science
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ACS Style

Takahiro Ukai; Hossein Zare-Behtash; Konstantinos Kontis; Leichao Yang; Erinc Erdem. Experimental investigation of surface flow pattern on truncated cones in Mach 5 flow: Influence of truncation ratio. Experimental Thermal and Fluid Science 2017, 81, 396 -405.

AMA Style

Takahiro Ukai, Hossein Zare-Behtash, Konstantinos Kontis, Leichao Yang, Erinc Erdem. Experimental investigation of surface flow pattern on truncated cones in Mach 5 flow: Influence of truncation ratio. Experimental Thermal and Fluid Science. 2017; 81 ():396-405.

Chicago/Turabian Style

Takahiro Ukai; Hossein Zare-Behtash; Konstantinos Kontis; Leichao Yang; Erinc Erdem. 2017. "Experimental investigation of surface flow pattern on truncated cones in Mach 5 flow: Influence of truncation ratio." Experimental Thermal and Fluid Science 81, no. : 396-405.

Journal article
Published: 01 December 2016 in Flow Measurement and Instrumentation
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Depending on the case study examined, different PSPs may be used, each applied using a different method onto the model. For polymer PSP the paint is sprayed on. In contrast, the model may first be anodised or covered with a thin-layer chromatography plate and then dipped in PSP. The objective of the present study is to analyse the characteristics of different PSP substrates at high Mach numbers which use two well-known PSP molecules: (i) tris-Bathophenanthroline Ruthenium (II) Perchlorate and (ii) Platinum-tetrakis (pentafluorophenyl) Porphyrin. Using a double ramp geometry under a Mach 5 hypersonic flow the feasibility of applying each of the aforementioned PSP methods is investigated and compared to discrete pressure measurements. The flow over a 3D bump under a Mach 1.3 flow is also studied to give a broader Mach number range. In the hypersonic tunnel, all PSP techniques and formulations were able to capture the complex flowfield with the results quantitatively agreeing with the discrete measurements. For the transonic bumps however, it was found that the polymer based Platinum PSP could map the flowfield more accurately.

ACS Style

H. Zare-Behtash; K.H. Lo; L. Yang; K. Kontis. Pressure sensitive paint measurements at high Mach numbers. Flow Measurement and Instrumentation 2016, 52, 10 -16.

AMA Style

H. Zare-Behtash, K.H. Lo, L. Yang, K. Kontis. Pressure sensitive paint measurements at high Mach numbers. Flow Measurement and Instrumentation. 2016; 52 ():10-16.

Chicago/Turabian Style

H. Zare-Behtash; K.H. Lo; L. Yang; K. Kontis. 2016. "Pressure sensitive paint measurements at high Mach numbers." Flow Measurement and Instrumentation 52, no. : 10-16.

Journal article
Published: 01 December 2016 in Experimental Thermal and Fluid Science
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ACS Style

Takahiro Ukai; Hossein Zare-Behtash; Konstantinos Kontis; Shigeru Obayashi. Three-dimensional shock wave distortion in shock-square vortex loop interaction. Experimental Thermal and Fluid Science 2016, 79, 85 -90.

AMA Style

Takahiro Ukai, Hossein Zare-Behtash, Konstantinos Kontis, Shigeru Obayashi. Three-dimensional shock wave distortion in shock-square vortex loop interaction. Experimental Thermal and Fluid Science. 2016; 79 ():85-90.

Chicago/Turabian Style

Takahiro Ukai; Hossein Zare-Behtash; Konstantinos Kontis; Shigeru Obayashi. 2016. "Three-dimensional shock wave distortion in shock-square vortex loop interaction." Experimental Thermal and Fluid Science 79, no. : 85-90.

Journal article
Published: 01 September 2016 in Acta Astronautica
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Flow separation control over a three-dimensional contour bump using jet in a Mach 1.9 supersonic free-stream has been experimentally investigated using a transonic/supersonic wind tunnel. Jet total pressure in the range of 0 bar to 4 bar was blowing at the valley of the contour bump. Schlieren photography, surface oil flow visualization and particle image velocimetry measurements were employed for flow visualization and diagnostics. Experimental results show that blowing jet at the valley of the contour bump can hinder the formation and distort the spanwise vortices. The blowing jet can also reduce the extent of flow separation appears downstream of the bump crest. It was observed that this approach of flow control is more effective when high jet total pressure is employed. It is believed that a pressure gradient is generated as a result of the interaction between the flow downstream of the bump crest and the jet induced shock leads to the downwards flow motion around the bump valley.

ACS Style

Kin Hing Lo; Hossein Zare-Behtash; Konstantinos Kontis. Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: An experimental study. Acta Astronautica 2016, 126, 229 -242.

AMA Style

Kin Hing Lo, Hossein Zare-Behtash, Konstantinos Kontis. Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: An experimental study. Acta Astronautica. 2016; 126 ():229-242.

Chicago/Turabian Style

Kin Hing Lo; Hossein Zare-Behtash; Konstantinos Kontis. 2016. "Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: An experimental study." Acta Astronautica 126, no. : 229-242.

Journal article
Published: 01 September 2016 in Acta Astronautica
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ACS Style

R. Ruisi; Hossein Zare-Behtash; Konstantinos Kontis; Rasool Erfani. Active flow control over a backward-facing step using plasma actuation. Acta Astronautica 2016, 126, 354 -363.

AMA Style

R. Ruisi, Hossein Zare-Behtash, Konstantinos Kontis, Rasool Erfani. Active flow control over a backward-facing step using plasma actuation. Acta Astronautica. 2016; 126 ():354-363.

Chicago/Turabian Style

R. Ruisi; Hossein Zare-Behtash; Konstantinos Kontis; Rasool Erfani. 2016. "Active flow control over a backward-facing step using plasma actuation." Acta Astronautica 126, no. : 354-363.

Conference paper
Published: 10 June 2016 in 8th AIAA Flow Control Conference
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Naser H. Al Haddabi; Sebastian Wiinblad-Rasmussen; Konstantinos Kontis; Hossein Zare-Behtash. Control of Low-Speed Cavity Flow Using Steady Jets. 8th AIAA Flow Control Conference 2016, 1 .

AMA Style

Naser H. Al Haddabi, Sebastian Wiinblad-Rasmussen, Konstantinos Kontis, Hossein Zare-Behtash. Control of Low-Speed Cavity Flow Using Steady Jets. 8th AIAA Flow Control Conference. 2016; ():1.

Chicago/Turabian Style

Naser H. Al Haddabi; Sebastian Wiinblad-Rasmussen; Konstantinos Kontis; Hossein Zare-Behtash. 2016. "Control of Low-Speed Cavity Flow Using Steady Jets." 8th AIAA Flow Control Conference , no. : 1.