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In this paper, the unsteady wake of a simplified square-back vehicle, with and without wheels, is investigated using large-scale tomographic particle image velocimetry, at a Reynolds number of$Re_{H}=5.78\\times 10^{5}$(based on the model height). In the no-wheel case, the time-averaged wake features a balanced toroidal shape, with a good level of symmetry in both vertical and lateral directions. However, analysis of the wake dynamics shows this widely accepted result to be a poor model of the wake structure. Application of proper orthogonal decomposition to the unsteady data reveals the existence of the widely reported bi-stable behaviour, consisting of random switches between two lateral symmetry-breaking states. For the first time, the three-dimensional topology of each state is fully characterised and the changes in wake topology during the switches between bi-stable states are also described. Each symmetry-breaking state is shown to feature a characteristic ‘hairpin vortex’ structure that is the result of the merging of two horseshoe vortices, aligned with the vertical edges of the model base. The mutual interactions between these vortices are found to be at the origin of the bi-stable mode. The vertical symmetry is lost when wheels are added to the model, resulting in the formation of an upwash-dominated wake. The bi-stable behaviour is removed but considerable mobility in the near wake remains, in the form of a swinging motion of the rear recirculation.

This study topologically describes near-wall flows around a surface-mounted cylinder at a high Reynolds number ($Re$) of $5\\times 10^4$ and in a very thick boundary layer, which were partially measured or technically approximated from the literature. For complete and rational flow construction, we use high-resolution simulations and critical-point theory. The large-scale near-wake vortex is composed of two connected segments rolled up from the sides of the cylinder and from the free end. Another large-scale side vortex clearly roots on two notable foci on the lower side wall. In the junction region, the side vortex moves upwards with a curved trajectory, which induces the formation of nodes on the ground surface. In the free-end region, the side vortex is compressed, which results in a smaller trailing-edge vortex and its downstream movement. Only tip vortices are observed in the far wake. The origin of the tip vortices and their distinction from the near-wake vortex are discussed. Further analyses suggest that $Re$ independence should be treated with high caution when $Re$ increases from 500 to ${O}(10^4)$. The occurrence of upwash flow behind the cylinder strongly depends on the increase in $Re$, the mechanism of which is also provided. The separation–reattachment process in the junction region and the trailing-edge vortices are discovered only at a high $Re$. The former should significantly affect the strength of the side vortex in the junction region and the latter should cause a sharp drop in pressure near the trailing edge.

For modern advanced turbofan engines, the increasing broadband noise of the fan/compressor has become an urgent problem. Based on the 3D fan sound source model, the numerical simulation of the effect of geometric parameters on broadband noise prediction is studied. As a result, (1) the three parameters change the sound power level by affecting the kernel function or the upwash velocity spectrum, and the influence laws are different. (2) If the kernel function is affected, the shape and size of the sound power level spectrum will change; if the upwash velocity spectrum is affected, only the sound power level is changed and the spectrum shape is basically unchanged. (3) The number of rotors only affects the upwash velocity spectrum; the number of stators and the chord length of stators only affect the kernel function.

Scaling laws for the thrust production and energetics of self-propelled or fixed-velocity three-dimensional rigid propulsors undergoing pitching motions are presented. The scaling relations extend the two-dimensional scaling laws presented in Moored & Quinn (AIAA J., 2018, pp. 1–15) by accounting for the added mass of a finite-span propulsor, the downwash/upwash effects from the trailing vortex system of a propulsor and the elliptical topology of shedding trailing-edge vortices. The novel three-dimensional scaling laws are validated with self-propelled inviscid simulations and fixed-velocity experiments over a range of reduced frequencies, Strouhal numbers and aspect ratios relevant to bio-inspired propulsion. The scaling laws elucidate the dominant flow physics behind the thrust production and energetics of pitching bio-propulsors, and they provide guidance for the design of bio-inspired propulsive systems.

Large-eddy simulation is combined with the Ffowcs Williams–Hawkings equation to investigate the noise generation by a 10-bladed rotor ingesting the turbulent wake of a circular cylinder in a low-Mach-number flow. Two rotor advance ratios corresponding to zero thrust and a thrusting condition are considered. The computed sound pressure levels agree well with the experimental measurements at Virginia Tech over a wide range of frequencies. The broadband acoustic spectra exhibit a strong tonal peak at the cylinder vortex-shedding frequency, a second peak at the rotor blade passing frequency, and a minor peak at the trailing-edge vortex-shedding frequency. Consistent with experimental results, the rotor at the thrusting advance ratio produces stronger sound than that at zero thrust. The blade acoustic dipole strength increases with the radial distance to the hub until near the blade tip. Fluctuating velocities in the wake are responsible for virtually all the rotor acoustic response except at the blade-passing frequency, where the mean wake velocity defect also makes a strong contribution. Blade-to-blade correlations and coherence of dipole sources are relatively weak. The classical Sears theory is shown to provide a reasonable prediction of the rotor turbulence-ingestion noise at the important mid-frequencies, based on which the appropriate Mach number scaling for the ingestion noise is identified. Distortions of wake turbulence by the rotor are found to be relatively small, and including their effect on the upwash velocity only slightly improves the Sears theory prediction.

An analytical model is developed for the prediction of noise radiated by an aerofoil with leading-edge serration in a subsonic turbulent stream. The model makes use of Fourier expansion and Schwarzschild techniques in order to solve a set of coupled differential equations iteratively and express the far-field sound power spectral density in terms of the statistics of incoming turbulent upwash velocity. The model has shown that the primary noise-reduction mechanism is due to the destructive interference of the scattered pressure induced by the leading-edge serrations. It has also shown that in order to achieve significant sound reduction, the serration must satisfy two geometrical criteria related to the serration sharpness and hydrodynamic properties of the turbulence. A parametric study has been carried out and it is shown that serrations can reduce the overall sound pressure level at most radiation angles, particularly at small aft angles. The sound directivity results have also shown that the use of leading-edge serration does not significantly change the dipolar pattern of the far-field noise at low frequencies, but it changes the cardioid directivity pattern associated with radiation from straight-edge scattering at high frequencies to a tilted dipolar pattern.

The wake of a long rectangular wall-mounted prism is investigated at Reynolds numbers of $Re=250\\unicode{x2013}1200$ by directly solving the Navier–Stokes equations. The aim of this study was to examine the unsteady transition mechanism in the wake of a large-depth-ratio (streamwise length to width) prism as well as to characterize the unsteady wake evolution at low Reynolds numbers. The results highlighted that increasing Reynolds number significantly altered the dominance of upwash and downwash flows in the time-averaged flow and changed the characteristics of coherent structures, including their size, dominant frequency and interaction with other structures in the flow. The wake is, therefore, categorized into three regimes within the transition process: steady regime at $Re \\leq 625$, regular unsteady regime at $625 < Re < 750$ and irregular unsteady regime at $Re \\geq 750$. Particularly, the wake started to exhibit unsteady features at $Re=625\\unicode{x2013}650$, which transitioned to an early irregular unsteady wake topology at $Re=750$. At $Re \\geq 675$, horseshoe vortices transformed to vortex loops. There were hairpin-like structures formed on the upper and side faces of the long prism. The results further indicated that the transition to unsteadiness is attributed to separated leading-edge shear-layer instabilities and interactions of the shear layer with the horseshoe structures. The wake was more complex due to the interactions of multiple coherent structures in the flow, which resulted in a multiple-periodicity wake system. A skeleton model is proposed for a large-depth-ratio prism, to incorporate details of the unsteady flow features and specify various flow coherent structures at low Reynolds numbers.

We investigate the behaviour of large-scale coherent structures in a spanwise-heterogeneous turbulent boundary layer, using particle image velocimetry on multiple orthogonal planes. The statistical three-dimensionality is imposed by a herringbone riblet surface, although the key results presented here will be common to many cases of wall turbulence with embedded secondary flows in the form of mean streamwise vortices. Instantaneous velocity fields in the logarithmic layer reveal elongated low-momentum streaks located over the upwash-flow region, where their spanwise spacing is forced by the $2\\unicode[STIX]{x1D6FF}$ periodicity of the herringbone pattern. These streaks largely resemble the turbulence structures that occur naturally (and randomly located) in spanwise-homogeneous smooth-/rough-wall boundary layers, although here they are directly formed by the roughness pattern. In the far outer region, the large spanwise spacing permits the streaks to aggressively meander. The mean secondary flows are the time-averaged artefact of the unsteady and spanwise asymmetric large-scale roll modes that accompany these meandering streaks. Interestingly, this meandering, or instability, gives rise to a pronounced streamwise periodicity (i.e. an alternating coherent pattern) in the spatial statistics, at wavelengths of approximately 4.5 $\\unicode[STIX]{x1D6FF}$ . Overall, the observed behaviours largely resemble the streak-instability model that has been proposed for the buffer region, only here at a much larger scale and at a forced spanwise spacing. This observation further confirms recent observations that such features may occur at an entire hierarchy of scales throughout the turbulent boundary layer.

During stroke reversals, insect wings interact with their own wake flow from the preceding half-stroke, resulting in an unsteady aerodynamic mechanism known as ‘wing–wake interaction’ or ‘wake capture’. To better elucidate this mechanism, we numerically solved the incompressible Navier–Stokes equations at Reynolds numbers $10^2$ and $10^3$. Simulations were conducted for wing planforms defined using the beta function distribution with varying aspect ratios ($AR=2\\unicode{x2013}6$) and radial centroid locations ($\\hat {r}_1=0.4\\unicode{x2013}0.6$), whilst employing representative normal hovering kinematics. The wake development from the considered flapping wing planforms was investigated, and the wake capture contribution to aerodynamic force production was quantified by comparing the force generation between the fifth and first stroke cycles at multiple sections along the wingspan. Our results revealed that on the inboard wing region experiencing an attached leading-edge vortex (LEV) structure, wing–wake interaction is dominated by an unsteady downwash effect, resulting in a reduction in local force production. However, in regions closer to the wingtip experiencing detachment of the LEV, wing–wake interaction is dominated by an unsteady upwash effect, leading to an increase in local force production. Consequently, the global wake capture force production is controlled by the extent of LEV detachment, which primarily increases with the increase of wing aspect ratio. This suggests that for normal hovering flapping wings, the typical loss in translational force production due to wingtip stall is partially mitigated by wake capture effects.

Microvortex generators are passive control devices smaller than the boundary layer thickness that energise the boundary layer to prevent flow separation with limited induced drag. In this work, we use direct numerical simulations (DNS) to investigate the effect of the Reynolds number in a supersonic turbulent boundary layer over a microramp vortex generator. Three friction Reynolds numbers are considered, up to $Re_\\tau = 2000$, for fixed free stream Mach number $M_\\infty =2$ and fixed relative height of the ramp with respect to the boundary layer thickness. The high-fidelity data set sheds light on the instantaneous and highly three-dimensional organisation of both the wake and the shock waves induced by the microramp. The full access to the flow field provided by DNS allows us to develop a qualitative model of the near wake, explaining the internal convolution of the Kelvin–Helmholtz vortices around the low-momentum region behind the ramp. The overall analysis shows that numerical results agree excellently with recent experimental measurements in similar operating conditions and confirms that microramps effectively induce a significantly fuller boundary layer even far downstream of the ramp. Moreover, results highlight significant Reynolds number effects, which in general do not scale with the ramp height. Increasing Reynolds number leads to enhanced coherence of the typical vortical structures in the field, faster and stronger development of the momentum deficit region, increased upwash between the primary vortices from the sides of the ramp – and thus increased lift-up of the wake – and faster transfer of momentum towards the wall.