Dissertations / Theses on the topic 'Boundary-Layer Instability'

The rotating-disk boundary layer is not only a simpler model for the study of cross-flow instability than swept-wing boundary layers but also a useful simplification of many industrial-flow applications where rotating configurations are present. For the rotating disk, it has been suggested that a local absolute instability, leading to a global instability, is responsible for the small variation in the observed laminar-turbulent transition Reynolds number however the exact nature of the transition is still not fully understood. This thesis aims to clarify certain aspects of the transition process. Furthermore, the thesis considers the turbulent rotating-disk boundary layer, as an example of a class of three-dimensional turbulent boundary-layer flows. The rotating-disk boundary layer has been investigated in an experimental apparatus designed for low vibration levels and with a polished glass disk that gave a smooth surface. The apparatus provided a low-disturbance environment and velocity measurements of the azimuthal component were made with a single hot-wire probe. A new way to present data in the form of a probability density function (PDF) map of the azimuthal fluctuation velocity, which gives clear insights into the laminar-turbulent transition region, has been proposed. Measurements performed with various disk-edge conditions and edge Reynolds numbers showed that neither of these conditions a↵ect the transition process significantly, and the Reynolds number for the onset of transition was observed to be highly reproducible. Laminar-turbulent transition for a ‘clean’ disk was compared with that for a disk with roughness elements located upstream of the critical Reynolds number for absolute instability. This showed that, even with minute surface roughness elements, strong convectively unstable stationary disturbances were excited. In this case, breakdown of the flow occurred before reaching the absolutely unstable region, i.e. through a convectively unstable route. For the rough disk, the breakdown location was shown to depend on the amplitude of individual stationary vortices. In contrast, for the smooth (clean-disk) condition, the amplitude of the stationary vortices did not fix the breakdown location, which instead was fixed by a well-defined Reynolds number. Furthermore, for the clean-disk case, travelling disturbances have been observed at the onset of nonlinearity, and the associated disturbance profile is in good agreement with the eigenfunction of the critical absolute instability. Finally, the turbulent boundary layer on the rotating disk has been investigated. The azimuthal friction velocity was directly measured from the azimuthal velocity profile in the viscous sublayer and the velocity statistics, normalized by the inner scale, are presented. The characteristics of this three-dimensional turbulent boundary-layer flow have been compared with those for the two-dimensional flow over a flat plate and close to the wall they are found to be quite similar but with rather large differences in the outer region.

QC 20150119

Rotating-disk flow has been investigated not only as a simple model of cross flow instability to compare with swept-wing flow but also for industrial flow applications with rotating configurations. However the exact nature of laminar-turbulent transi- tion on the rotating-disk flow is still major problem and further research is required for it to be fully understood, in particular, the laminar-turbulent transition process with absolute instability. In addition the studies of the rotating-disk turbulent boundary- layer flow are inadequate to understand the physics of three-dimensional turbulent boundary-layer flow. In present thesis, a rotating-rotating disk boundary-layer flow has been inves- tigated experimentally using hot-wire anemometry. A glass disk with a flat surface has been prepared to archieve low disturbance rotating-disk environment. Azimuthal velocity measurements using a hot-wire probe have been taken for various conditions. To get a better insight into the laminar-turbulent transition region, a new way to describe the process is proposed using the probability density function (PDF) map of azimuthal fluctuation velocity. The effect of the edge of the disk on the laminar-turbulent transition process has been investigated. The disturbance growth of azimuthal fluctuation velocity as a function of Reynolds number has a similar trend irrespective of the various edge conditions. The behaviour of secondary instability and turbulent breakdown has been in- vestigated. It has been found that the kinked azimuthal velocity associated with secondary instability just before turbulent breakdown became less apparent at a cer- tain wall normal heights. Furthermore the turbulent breakdown of the stationary mode seems not to be triggered by its amplitude, however, depend on the appearance of the travelling secondary instability. Finally, the turbulent boundary layer on a rotating disk has been investigated. An azimuthal friction velocity has been directly measured from the azimuthal velocity profile in the viscous sub-layer. The turbulent statistics normalized by the inner and outer sclaes are presented.
QC 20120529

The subharmonic instability in two-dimensional boundary layer on a flat plate is analyzed using the parametric instability model and the resonant triad model. The problems arising from both models are solved numerically using the shooting technique and results are presented. It is found that in the presence of a strong interaction (e.g., large amplitude of the two-dimensional wave), results from the resonant triad model are inaccurate as compared with the experimental data and the t results from the parametric instability model. This is mainly because the resonant triad model is a weakly nonlinear model, and it does not account for the modification of the eigenfunctions of the interacting waves which really takes place as we find out from the experiments.

The parametric instability model is a powerful model, despite all the assumptions included. The model, however, does not introduce a clear understanding of how the subharmonic mode originates from the three-dimensional Tollmien-Schlichting modes.

For a weak interaction results from the resonant triad model and the parametric instability model get close to each other.

Master of Science

This thesis deals with the instabilities of the incompressible boundary-layer flow thatis induced by a disk rotating in otherwise still fluid. The results presented include bothwork in the linear and nonlinear regime and are derived from direct numerical sim-ulations (DNS). Comparisons are made both to theoretical and experimental resultsproviding new insights into the transition route to turbulence. The simulation codeNek5000 has been chosen for the DNS using a spectral-element method (SEM) witha high-order discretization, and the results were obtained through large-scale paral-lel simulations. The known similarity solution of the Navier–Stokes equations for therotating-disk flow, also called the von K ́arm ́an rotating-disk flow, is reproduced by theDNS. With the addition of modelled small simulated roughnesses on the disk surface,convective instabilities appear and data from the linear region in the DNS are anal-ysed and compared with experimental and theoretical data, all corresponding verywell. A theoretical analysis is also presented using a local linear-stability approach,where two stability solvers have been developed based on earlier work. Furthermore,the impulse response of the rotating-disk boundary layer is investigated using DNS.The local response is known to be absolutely unstable and the global response, onthe contrary, is stable if the edge of the disk is assumed to be at radius infinity. Herecomparisons with a finite domain using various boundary conditions give a globalbehaviour that can be both linearly stable and unstable, however always nonlinearlyunstable. The global frequency of the flow is found to be determined by the Rey-nolds number at the confinement of the domain, either by the edge (linear case) or bythe turbulence appearance (nonlinear case). Moreover, secondary instabilities on topof the convective instabilities induced by roughness elements were investigated andfound to be globally unstable. This behaviour agrees well with the experimental flowand acts at a smaller radial distance than the primary global instability. The sharpline corresponding to transition to turbulence seen in experiments of the rotating diskcan thus be explained by the secondary global instability. Finally, turbulence datawere compared with experiments and investigated thoroughly.

QC 20170203

This thesis deals with the instabilities of the incompressible boundary-layer flow that is induced by a disk rotating in otherwise still fluid. The results presented are mostly limited to linear instabilities derived from direct numerical simulations (DNS) but with the objective that further work will focus on the nonlinear regime, providing greater insights into the transition route to turbulence. The numerical code Nek5000 has been chosen for the DNS using a spectral-element method in an effort to reduce spurious effects from low-order discretizations. Large-scale parallel simulations have been used to obtain the present results. The known similarity solution of the Navier–Stokes equation for the rotating-disk flow, also called the von Karman flow, is investigated and can be reproduced with good accuracy by the DNS. With the addition of small roughnesses on the disk surface, convective instabilities appear and data from the DNS are analysed and compared with experimental and theoretical data. A theoretical analysis is also presented using a local linear-stability approach, where two stability solvers have been developedbased on earlier work. A good correspondence between DNS and theory is found and the DNS results are found to explain well the behaviour of the experimental boundary layer within the range of Reynolds numbers for small amplitude (linear) disturbances. The comparison between the DNS and experimental results, presented for the first time here, shows that the DNS allows (for large azimuthal domains) a range of unstable azimuthal wavenumbers β to exist simultaneously with the dominantβ varying, which is not accounted for in local theory, where β is usually fixed for each Reynolds number at which the stability analysis is applied. Furthermore, the linear impulse response of the rotating-disk boundary layer is investigated using DNS. The local response is known to be absolutely unstable. The global response is found to be stable if the edge of the disk is assumed to be at infinity, and unstable if the domain is finite and the edge of the domain is placed such that there is a large enough pocket region for the absolute instability to develop. The global frequency of the flow is found to be determined by the edge Reynolds number.

QC 20140708

The linear instability of laterally diverging/converging flows is an important aspect towards understanding the laminar-transition process in many viscous flows. In this work the linear instability of constant pressure laterally diverging/converging flow has been investigated. The laminar velocity field for laterally diverging/converging flows, under the source/sink approximation, has been reduced to two-dimensional flows. This reduction is alternative to the Mangier transformation used earlier. For a constant pressure laterally strained flow, the laminar velocity is found to be governed by the Blasius equation for flow over a flat plate. The non-parallel linear instability of constant pressure laterally strained flows has been examined. The instability equation is found to be same as that for the Blasius flow. This implies that the stability is same as that for the Blasius flow. A lateral divergence/convergence is shown to alter the Reynolds number from that in a two-dimensional flow. The instability of a laterally converging/diverging flow thus can be obtained from the available results for the Blasius flow by scaling the Reynolds numbers. This leads to the result that while a diverging flow is more unstable than the Blasius flow, a converging flow is more stable. Some additional relevant results are also presented.

In this thesis, the main focus is on the interaction of an incoming Tollmien–Schlichting wave with an isolated, stationary wall roughness in subsonic flow. In Part I, this problem is analysed by means of the Triple Deck theory. The linearised sublayer equations are solved under the assumption that the horizontal extent of the roughness is of O(L Re^(−3/8)) and that its height h is small, and an expression for the pressure perturbation is found. The transmission coefficient T_I , defined as the amplitude of the T–S wave downstream of the roughness divided by its initial amplitude, is then calculated, where |T_I | > 1 means that the wave is amplified and |T_I | < 1 represents an attenuation of the T–S wave. The transmission coefficient is dependent on the frequency ω, the height h of the roughness and on the Fourier transform of the roughness shape evaluated at zero value of the wavenumber. The same setup is investigated in Part II through numerical calculations: a DNS solver provides the base flows for 25 different gaps of varying width and height, which are then run through a PSE analysis to examine the stability of the flow. From the results of both methods it can be concluded that a surface indentation amplifies an incoming T–S wave, and that the amplification increases with the width and depth of the roughness. An additional geometry is studied in Part I by again employing the Triple Deck theory to investigate the effect small elastic vibrations of a semi-infinite plate attached to a stationary plate have on the boundary layer, and the receptivity coefficient is calculated for varying ω.

An investigation of the influence of various wall perturbations on the development of instability waves has been carried out through a series of experiments to study different aspects of the stability/transition problem. The first experiment was devoted to an investigation of the effects of an isolated step on the transition of the boundary layer over a flat plate. Steps of various heights, both positive and negative, produced an upstream movement of the transition point, which was interpreted as arising from an increase in the amplification of the instability waves. The transition Reynolds number and the resulting change in the so-called 'N-factor', used for transition prediction, has been correlated with the step height to provide a useful empirical engineering design tool. The second experiment concerned the effect of a two-dimensional (2-D) sharpedged short bump on instability waves (Tollmien-Schlichting (TS) waves). The experiment was designed to study the mechanisms by which a sharp-edged surface roughness element, in the form of a 2-D bump, modified the evolution of TS wave and hence affected the process of transition. This investigation demonstrated that the interaction of a 2-D TS wave with a 2-D bump was a many-sided complex problem. The bump played multiple roles as a disturbance generator, an amplifier and a promoter of three-dimensionality. The crucial parameter was the height. Nonlinearity was the main factor that caused the enhancement of boundary layer transition and manifested itself in the appearance of higher harmonics in the spectra. In the last experiment the bump was three-dimensional (3-D) and in the form of a cylinder. The experimental results revealed that the effect of a 3-D bump was confined to a wedge-shaped region downstream of the bump. The mean velocity distortion had a distinct spanwise distribution from which a pair of streamwise vortex structures could be inferred. The interaction of a 2-D TS wave with a 3-D bump generated oblique waves with a dominant band of spanwise wavenumbers as predicted by theoretical analysis. Three thresholds were found that defined bump height ranges where there was no-effect, a linear behaviour and a nonlinear one.

A lot has changed since that day on December 17, 1903 when the Wright brothers made the first powered manned flight. Even though the concepts behind flying are unaltered, appearance of stat-of-the-art modern aircrafts has undergone a massive evolution. This is mainly owed to our deeper understanding of how to harness and optimize the interaction between fluid flows and aircraft bodies. Flow passing over wings and different junctions on an aircraft faces numerous local features, for instance, acceleration or deceleration, laminar or turbulent state, and interacting boundary layers. In our study we aim to characterize some of these flow features and their physical roles. Primarily, stability characteristics of flow over a wing subject to a negative pressure gradient are studied. This is a common condition for flows over swept wings. Part of the current numerical study conforms to existing experimental studies where a passive control mechanism has been tested to delay laminarturbulent transition. The same flow type has also been considered to study the receptivity of three-dimensional boundary layers to freestream turbulence. The work entails investigation of effects of low-level freestream turbulence on crossflow instability, as well as interaction with micron-sized surface roughness elements. Another common three-dimensional flow feature arises as a resultof stream-lines passing through a junction, the so-calledcorner-flow. For instance, thisflow can be formed in the junction between the wing and fuselage on aplane.A series of direct numerical simulations using linear Navier-Stokes equationshave been performed to determine the optimal initial perturbation. Optimalrefers to perturbations which can gain the maximum energy from the flow overa period of time. In other words this method seeks to determine theworst-casescenario in terms of perturbation growth. Here, power-iterationtechnique hasbeen applied to the Navier-Stokes equations and their adjoint to determine theoptimal initial perturbation. Recent advances in super-computers have enabled advance computational methods to increasingly contribute to design of aircrafts, in particular for turbulent flows with regions of separation. In this work we investigate theturbulentflow on an infinite wing at a moderate chord Reynolds number of Re= 400,000 using a well resolved direct numerical simulation. A conventional NACA4412 has been chosen for this work. The turbulent flow is characterizedusing statistical analysis and following time history data in regions with interesting flow features. In the later part of this work, direct numerical simulation has been chosen as a tool to mainly investigate the effect of freestream turbulence on the transition mechanism of flow from laminar to turbulent around a turbine blade.

QC 20151125

The majority of this work is concerned with the local-linear convective instability analysis of the incompressible boundary-layer flows over prolate spheroids and oblate spheroids rotating in otherwise still fluid. The laminar boundary layer and the perturbation equations have been formulated by introducing two distinct orthogonal coordinate systems. A cross-sectional eccentricity parameter e is introduced to identify each spheroid within its family. Both systems of equations reduce exactly to those already established for the rotating sphere boundary layer. The effects of viscosity and streamline-curvature are included in each analysis. We predict that for prolate spheroids at low to moderate latitudes, increasing eccentricity has a strong stabilizing effect. However, at high latitudes of ϴ ≥ 60, increasing eccentricity is seen to have a destabilizing effect. For oblate spheroids, increasing eccentricity has a stabilizing effect at all latitudes. Near the pole of both types of spheroids, the critical Reynolds numbers approach that for the rotating disk boundary layer. However, in prolate spheroid case near the pole for very large values of e, the critical Reynolds numbers exceed that for the rotating disk. We show that high curvature near the pole of prolate spheroids is responsible for the increase in critical Reynolds number with increasing eccentricity. For both types of spheroids at moderate eccentricity, we predict that the most amplified modes travel at approximately 76% of the surface speed at all latitudes. This is consistent with the existing studies of boundary-layer flows over the related rotating-disk, -sphere and -cone geometries. However, for large values of eccentricity, the traveling speed of the most amplified modes increases up to approximately 90% of the surface speed of oblate spheroids and up to 100% in the prolate spheroid case.

The BEK family of flows have many important practical applications such as centrifugal pumps, steam turbines, turbo-machinery and rotor-stator devices. The Bödewadt, Ekman and von Kármán flows are particular cases within this family. The convective instability of the BEK family of rotating boundary-layer flows has been considered for generalised Newtonian fluids, power-law and Carreau fluids. A linear stability analysis is conducted using a Chebyshev collocation method in order to investigate the effect of shear-thinning and shear-thickening fluids for generalised Newtonian fluids on the convective Type I (inviscid crossflow) and Type II (viscous streamline curvature) modes of instability. The results reveal that shear-thinning power-law fluids have a universal stabilising effect across the entire BEK family of flows. However, the convective instability characteristics for the shear-thinning and shear-thickening Carreau fluids are affected by the value of the relaxation parameter k. The results reveal that Shear-thinning Carreau fluids have a small destabilising effect, while shear -thickening fluids have a slight stabilising effect on the Type I and Type II mode for the BEK family of flows when k =100. On the other hand, shear-thinning and shear-thickening Carreau fluids are found to have stabilising and destabilising effect, respectively for optimal relaxation value ko. The results are presented in terms of neutral curves and growth rates. Furthermore, an energy analysis is presented to gain insight into the underlying physical mechanisms behind the stabilising effects of generalized Newtonian fluids. In conclusion, the use of shear-thinning power-law and Carreau fluids with optimal value ko can be recommended to reduce skin-friction drag in enclosed rotor-stator devices for the entire BEK family of flows.

Determining the factors affecting drizzle formation in marine boundary layer (MBL) clouds remains a challenge for both observation and modeling communities. To investigate the roles of vertical wind shear and buoyancy (static instability) in drizzle formation, ground-based observations from the Atmospheric Radiation Measurement Program at the Azores are analyzed for two types of conditions. The type I clouds should last for at least 5h and more than 90% time must be nondrizzling and then followed by at least 2h of drizzling periods, while the type II clouds are characterized by mesoscale convection cellular structures with drizzle occur every 2 to 4h. By analyzing the boundary layer wind profiles (direction and speed), it was found that either directional or speed shear is required to promote drizzle production in the type I clouds. Observations and a recent model study both suggest that vertical wind shear helps the production of turbulent kinetic energy (TKE), stimulates turbulence within cloud layer, and enhances drizzle formation near the cloud top. The type II clouds do not require strong wind shear to produce drizzle. The small values of lower tropospheric stability (LTS) and negative Richardson number (R-i) in the type II cases suggest that boundary layer instability plays an important role in TKE production and cloud-drizzle processes. By analyzing the relationships between LTS and wind shear for all cases and all time periods, a stronger connection was found between LTS and wind directional shear than that between LTS and wind speed shear.

Experimental findings show that transition from laminar toturbulent ow may occur also if the exponentially growingperturbations, eigensolutions to the linearised disturbanceequations, are damped. An alternative non-modal growthmechanism has been recently identi fied, also based on thelinear approximation. This consists of the transient growth ofstreamwise elongated disturbances, with regions of positive andnegative streamwise velocity alternating in the spanwisedirection, called streaks. These perturbation are seen toappear in boundary layers exposed to signi ficant levels offree-stream turbulence. The effect of the streaks on thestability and transition of the Blasius boundary layer isinvestigated in this thesis. The analysis considers the steadyspanwise-periodic streaks arising from the nonlinear evolutionof the initial disturbances leading to the maximum transientenergy growth. In the absence of streaks, the Blasius pro filesupports the viscous exponential growth of theTollmien-Schlichting waves. It is found that increasing thestreak amplitude these two-dimensional unstable waves evolveinto three-dimensional spanwiseperiodic waves which are lessunstable. The latter can be completely stabilised above athreshold amplitude. Further increasing the streak amplitude,the boundary layer is again unstable. The new instability is ofdifferent character, being driven by the inectional pro filesassociated with the spanwise modulated ow. In particular, it isshown that, for the particular class of steady streaksconsidered, the most ampli fied modes are antisymmetric andlead to spanwise oscillations of the low-speed streak (sinuousscenario). The transition of the streak is then characterisedby the appearance of quasi-streamwise vorticesfollowing themeandering of the streak.

Simulations of a boundary layer subjected to high levels offree-stream turbulence have been performed. The receptivity ofthe boundary layer to the external perturbation is studied indetail. It is shown that two mechanisms are active, a linearand a nonlinear one, and their relative importance isdiscussed. The breakdown of the unsteady asymmetric streaksforming in the boundary layer under free-stream turbulence isshown to be characterised by structures similar to thoseobserved both in the sinuous breakdown of steady streaks and inthe varicose scenario, with the former being the mostfrequently observed.

Keywords:Fluid mechanics, laminar-turbulent transition,boundary layer ow, transient growth, streamwise streaks,lift-up effect, receptivity, free-stream turbulence, secondaryinstability, Direct Numerical Simulation.

The effect of freestream turbulence on generation of crossflow disturbances over swept wings is investigated through direct numerical simulations.  The set up follows  the  experiments  performed  by Downs  et  al.  in their  TAMU  experi- ment.  In this experiment the authors use ASU(67)-0315 wing geometry which promotes  growth  of crossflow  disturbances.   Distributed  roughness  elements are locally placed near the leading edge with a span-wise wavenumber, to ex- cite the corresponding crossflow vortices.  The response of boundary layer to external disturbances such as roughness heights, span-wise wavenumbers, Rey- nolds numbers and freestream turbulence characteristics are studied.  It must be noted that the experiments were conducted at a very low level of freestream turbulence  intensity  (T u).   In this  study,  we fully  reproduce the  freestream isotropic homogenous turbulence through a DNS code using detailed freestream spectrum data provided by the experiment. The generated freestream fields are then applied as the inflow boundary condition for direct numerical simulation of the wing. The geometrical set up is the same as the experiment along with application of distributed roughness elements near the leading edge to precipi- tate stationary crossflow disturbances.  The effects of the generated freestream turbulence are then studied on the initial amplitudes and growth of the bound- ary layer perturbations.  It appears that the freestream turbulence damps out the dominant stationary crossflow vortices.

QC 20130604

The focus of this thesis is on the numerical study of subcritical transition to turbulence in the asymptotic suction boundary layer (ASBL). Applying constant homogeneous suction prevents the spatial growth of the boundary layer, granting access to the asymptotic dynamics. This enables research approaches which are not feasible in the spatially growing case. In a first part, the laminar–turbulent separatrix of the ASBL is investigated numerically by means of an edge-tracking algorithm. The consideration of spanwise-extended domains allows for the robust localisation of the attracting flow structures on this separatrix. The active part of the identified edge states consists of a pair of low- and high-speed streaks, which experience calm phases followed by high energy bursts. During these bursts the structure is destroyed and re-created with a shift in the spanwise direction. Depending on the streamwise extent of the domain, these shifts are either regular in direction and distance, and periodic in time, or irregular in space and erratic in time. In all cases, the same clear regeneration mechanism of streaks and vor- tices is identified, bearing strong similarities with the classical self-sustaining cycle in near-wall turbulence. Bifurcations from periodic to chaotic regimes are studied by varying the streamwise length of the (periodic) domain. The resulting bifurcation diagram contains a number of phenomena, e.g. multistability, intermittency and period doubling, usually investigated in the context of low-dimensional systems. The second part is concerned with spatio–temporal aspects of turbulent ASBL in large domains near the onset of sustained turbulence. Adiabatically decreasing the Reynolds number, starting from a fully turbulent state, we study low-Re turbulence and events leading to laminarisation. Furthermore, a robust quantitative estimate for the lowest Reynolds number at which turbulence is sustained is obtained at Re  270.

QC 20140213

A numerical study investigating the effects of surface roughness on the stability properties of the BEK system of flows is introduced. The BEK system of flows occur in many engineering applications such as turbo-machinery and rotor-stator devices, therefore they have great practical importance. Recent studies have been concerned with the effects of surface roughness on the von Kármán flow. The aim of this thesis is to investigate whether distributed surface roughness could be used as a passive drag reduction technique for the broader BEK system of flows. If it can, what is “the right sort of roughness?" To answer these questions, a linear stability analysis is performed using the Chebyshev collocation method to investigate the effect of particular types of distributed surface roughness, both anisotropic and isotropic, on the convective instability characteristics of the inviscid Type I (cross-flow) instability and the viscous Type II instability. The results reveal that all roughness types lead to a stabilisation of the Type I mode in all flows within the BEK family, with the exception of azimuthally-anisotropic roughness (radial grooves) within the Bődewadt flow which causes a mildly destabilising effect. In the case of the Type II mode, the results reveal the destabilising effect of radially-anisotropic roughness (concentric grooves) on all the boundary layers, whereas both azimuthally-anisotropic and isotropic roughness have a stabilising effect on the mode for Ekman and von Kármán flows. Moreover, an energy analysis is performed to investigate the underlying physical mechanisms behind the effects of rough surfaces on the BEK system. The conclusion is that isotropic surface roughness is the most effective type of the distributed surface roughness and can be recommended as a passive-drag reduction mechanism for the entire BEK system of flows.

Transition from laminar to turbulent flow has beentraditionally studied in terms of exponentially growingeigensolutions to the linearized disturbance equations.However, experimental findings show that transition may occuralso for parameters combinations such that these eigensolutionsare damped. An alternative non-modal growth mechanism has beenrecently identified, also based on the linear approximation.This consists of the transient growth of streamwise elongateddisturbances, mainly in the streamwise velocity component,called streaks. If the streak amplitude reaches a thresholdvalue, secondary instabilities can take place and provoketransition. This scenario is most likely to occur in boundarylayer flows subject to high levels of free-stream turbulenceand is the object of this thesis. Different stages of theprocess are isolated and studied with different approaches,considering the boundary layer flow over a flat plate. Thereceptivity to free-stream disturbances has been studiedthrough a weakly non-linear model which allows to disentanglethe features involved in the generation of streaks. It is shownthat the non-linear interaction of oblique waves in thefree-stream is able to induce strong streamwise vortices insidethe boundary layer, which, in turn, generate streaks by thelift-up effect. The growth of steady streaks is followed bymeans of Direct Numerical Simulation. After the streaks havereached a finite amplitude, they saturate and a new laminarflow, characterized by a strong spanwise modulation isestablished. Using Floquet theory, the instability of thesestreaks is studied to determine the features of theirbreakdown. The streak critical amplitude, beyond which unstablewaves are excited, is 26% of the free-stream velocity. Theinstability appears as spanwise (sinuous-type) oscillations ofthe streak. The late stages of the transition, originating fromthis type of secondary instability, are also studied. We foundthat the main structures observed during the transition processconsist of elongated quasi-streamwise vortices located on theflanks of the low speed streak. Vortices of alternating signare overlapping in the streamwise direction in a staggeredpattern.

Descriptors:Fluid mechanics, laminar-turbulenttransition, boundary layer flow, transient growth, streamwisestreaks, lift-up effect, receptivity, free-stream turbulence,nonlinear mechanism, streak instability, secondary instability,Direct Numerical Simulation.

QC 20100518

The aim of this thesis is to describe the linear and non-linear dynamics of both attached and separated boundary-layer flows over a flat plate at low Reynolds numbers. The linear dynamics, driven by the interactions among the non-orthogonal eigenvectors, is studied using two global instability approaches: the global eigenvalue analysis and the direct-adjoint optimization. In these global instability analysis no spatial structure is assumed a-priori for the perturbation, and the convective effects due to the high non-parallelism of the flow are taken into account. In the case of the separated boundary-layer flows, it has been clarified the role of the following features in the onset of unsteadiness: i) the strong two-dimensional convective amplification; ii) the non-normality effects such as the 'flapping' phenomenon; iii) the high sensitivity to external forcing; iv) the globally unstable three-dimensional mode. Concerning the attached boundary layer, the aim has been to identify localized perturbations characterized by more than one frequency in the streamwise and/or spanwise direction, inducing a strong energy amplification. In order to assess the effects of non-linearity on the instability mechanisms identified by the global linear stability analysis, direct numerical simulations have been performed in a two- and three-dimensional framework for both the attached and separated boundary-layer flows. The dynamics of the perturbations which most easily brings the flows on the verge of turbulence have been studied. Different scenarios of transition have been observed, and the mechanisms leading the flow to turbulence have been analyzed in detail
Le but de cette thèse est de décrire en détail la dynamique linéaire et non linéaire d'une couche limite attachée sur une plaque plane à bas nombre de Reynolds. La dynamique linéaire, pilotée par les interactions entre les vecteurs propres non-orthogonaux, est étudiée à travers deux méthodes différentes d’instabilité globale : une analyse globale aux vecteurs propres et une optimisation directe-adjointe. Dans ces analyses globales, aucune structure spatiale n’est imposée à priori pour la perturbation, les effets convectifs dus au fort non parallélisme de l’écoulement sont pris en compte. Pour le cas de la couche limite décollée, le déclenchement des instationnarités a été clarifié : i) pour une forte amplification des perturbations de nature convective et bidimensionnelle ; ii) pour des effets de non normalité longitudinale engendrant le phénomène du flapping ; iii) pour une forte sensibilité vis-à-vis d’un forçage harmonique ; iv) pour un monde tridimensionnel globalement instable. Pour une couche limite attachée, le but a été d’identifier les perturbations localisées caractérisées par des fréquences multiples dans les directions longitudinales et transversales de l’écoulement, induisant une amplification de l’énergie des perturbations. Pour évaluer les effets les effets de la non linéarité dans les mécanismes d’instabilité identifiés par les analyses de stabilité globale, des simulations numériques directes ont été réalisées pour les écoulements de couche limite attachées ou décollées, bidimensionnelles et tridimensionnelles. La dynamique des perturbations permettant une plus rapide vers la turbulence a été étudiée. Différents scénarios de transition ont été observés, les différents mécanismes de transition ont été analysés

The viscous drag of a passenger aircraft is influenced significantly by the laminar-turbulent transition in the boundary-layer. Classically the transition process occurs when the turbulence develops as a result of the amplification of instability modes. In the flow past a unswept wing one such mode of instability is observed, Tollmien-Schlichting waves. We deal with the Tollmien-Schlichting waves or, more specifically, with the receptivity of the boundary layer with respect to them. If the surface becomes curved a different instability mode is created: Gortler vortices, which we will investigate as an inviscid secondary instability. Many disturbances can aid the generation of these instabilities but we concentrate on the vibrations of the wing caused by engine noise and the elasticity of the wing itself. This thesis is separated into these two problems of boundary-layer flow over the vibrating wing surface. Firstly we focus on the generation of Tollmien-Schlichting waves due to wing surface vibrations and surface roughness. Piston theory is used to describe the response of the flow outside the boundary layer to wing surface vibrations. Then the perturbations in the Stokes' layer are analysed. The Stokes' layer itself cannot produce a Tollmien-Schlichting wave. Therefore, we will assume that there is a wall roughness. The analysis of the interaction of the Stokes' layer with a wall roughness can be analysed with the help of the Triple deck theory. This allows us to consider the downstream effects of our disturbances and under our flow regime, dependent on the size of wavelength of vibrations, we can Fourier transform and solve our problem for the disturbance pressure. Once we have inverted our solution back into real space with the use of Residue theory we are then able to calculate receptivity coefficients which can be compared to those of previous studies. In the second problem we concentrate on the curved part of the wing where the flow is assumed to be slowly varying in the y direction. This generates Gortler vortices and we expect a sheared base flow with periodicity in the spanwise direction. Using a WKBJ approximation we can derive a multi-scale system of equations, which at leading order can be solved numerically to give eigenvalues and eigenfunctions representing pressure within the boundary-layer. We can only do so with the aid of a two-dimensional problem from which we fix an effective streamwise wavenumber, and an effective maximum growth rate. We use this to create an initial value for our WKBJ eigenvalue. This restricts the values of the streamwise wavenumber that we can calculate solutions for. This also means that when the streamwise wavenumber approaches the effective streamwise wavenumber we get a turning point and hence a breakdown of our WKBJ solutions. We derive and calculate solutions for streamwise wavenumbers away from this limit and discuss the breakdown of these solutions.

This thesis addresses the investigation of mechanisms involved in the transition from laminar to turbulent flow. The flow studied is a compressible flat plate boundary layer at a free stream velocity of M = 4.5. The two-dimensional compressible unsteady Navier Stokes equations are solved numerically in a rectangular region at a distance downstream from the leading edge. Disturbances are introduced by periodical suction and blowing through a slot in the wall. These disturbances propagate downstream in the flow field. At every point in the flow field the response of the flow is analyzed using a Fourier analysis in time. Results obtained are interpreted with reference to linear stability theory. One important result is the existence of multiple undamped waves for one wave frequency. The second important result demonstrates that an amplified wave of a certain frequency can generate disturbances at multiples of its frequency which may then be amplified more strongly.

This thesis considers the hydrodynamic instability and optimal forcing of a number of incompressible flow cases. In the first part, the instabilities of three problems that are of great interest in energy and aerospace applications are studied, namely a Blasius boundary layer subject to localized wall-suction, a Falkner–Skan–Cooke boundary layer with a localized surface roughness, and a pair of helical vortices. The two boundary layer flows are studied through spectral element simulations and eigenvalue computations, which enable their long-term behavior as well as the mechanisms causing transition to be determined. The emergence of transition in these cases is found to originate from a linear flow instability, but whereas the onset of this instability in the Blasius flow can be associated with a localized region in the vicinity of the suction orifice, the instability in the Falkner–Skan–Cooke flow involves the entire flow field. Due to this difference, the results of the eigenvalue analysis in the former case are found to be robust with respect to numerical parameters and domain size, whereas the results in the latter case exhibit an extreme sensitivity that prevents domain independent critical parameters from being determined. The instability of the two helices is primarily addressed through experiments and analytic theory. It is shown that the well known pairing instability of neighboring vortex filaments is responsible for transition, and careful measurements enable growth rates of the instabilities to be obtained that are in close agreement with theoretical predictions. Using the experimental baseflow data, a successful attempt is subsequently also made to reproduce this experiment numerically. In the second part of the thesis, a novel method for computing the optimal forcing of a dynamical system is developed. The method is based on an application of the inverse power method preconditioned by the Laplace preconditioner to the direct and adjoint resolvent operators. The method is analyzed for the Ginzburg–Landau equation and afterwards the Navier–Stokes equations, where it is implemented in the spectral element method and validated on the two-dimensional lid-driven cavity flow and the flow around a cylinder.

QC 20171124

La recherche présentée dans cette thèse se concentre sur la conception et l’utilisation d’actionneurs plasma à décharge à barrière diélectrique (DBD) de faible épaisseur et à géométrie complexe afin d’exercer un contrôle d’instabilité sur deux configurations d’écoulement dont la dynamique est régie par des mécanismes d’instabilités primaires et/ou secondaires. Le cas d’une couche limite tridimensionnelle telle que rencontrée sur une aile en flèche est étudié à l’aide de deux stratégies de forçage permettant de manipuler la transition induite par un phénomène d’instabilité stationnaire. Ici, un réseau d’éléments de rugosité discrets (DRE) est installé en amont du forçage par DBD afin de verrouiller l’origine et l’évolution des tourbillons stationnaires transversaux de la couche limite. La première approche de forçage consiste à modifier l’écoulement amont par déformation (UFD). Une seconde approche par modification directe de l’écoulement de base est également introduite (BFM). Un retard de transition est observé indépendamment du forçage réalisé. Cependant, comme les tourbillons transverses sont fortement amplifiés en raison de l’utilisation de DRE, l’action par approche UFD peut conduire à la fois à une atténuation directe des structures fluidiques transverses telle qu’envisagée mais aussi à une action non intentionnelle sur la nature inflectionnelle de l’écoulement de base. La méthode BFM résulte en une interaction directe sur les tourbillons transverses, interactions confirmées par une étude théorique de l’instabilité sous l’effet d’un modèle simplifié d’actionneur DBD. Il s’agit de la première démonstration expérimentale du retard de transition sur une aile en flèche grâce à l’effet d’un actionneur plasma et également à la première preuve de concept expérimentale de la stratégie BFM.Le sillage d’une couche de mélange plane à bord épais et les phénomènes d’instabilité primaire et secondaire responsables pour l’expansion spatio-temporelle du sillage sont également étudiés. Des conditions de forçage fréquentiel puis spatial sont successivement testées et analysées par approche spectrale (décomposition orthogonale spectrale, SPOD) sur des données expérimentales de PIV multi-champs résolues en temps. L’instabilité primaire est excitée par un forçage spatialement homogène pulsé à la fréquence naturellement la plus amplifiée. Ce forçage l’atténue les instabilités aux sous-harmoniques et inhibe l’appariement tourbillonnaires. A l’inverse, le forçage aux sous-harmoniques renforce les phénomènes d’appariement conduisant à un fort taux d’épanouissement de la couche de mélange. Enfin, l’effet d’un forçage modulé spatialement se traduit par un taux d’accroissement variant selon la position transverse et qui traduit à la fois le renforcement et la modulation spatiale des structures à grande échelle. La segmentation du forçage selonl’envergure de la couche de mélange permet toujours de modifier les structures transverses mais en sus, la coalescence des structures longitudinales et transversales est favorisée.Les travaux de recherche réalisés confirment la capacité des actionneurs plasma de type DBD à exercer un forçage modulé à la fois temporellement et spatialement. La large réduction de la puissance électrique consommée dans le cas d’un forçage modulé spatialement permet une amélioration notable de l’efficacité du système de contrôle
The research presented in this thesis focuses on the design and use of dielectric barrier discharge (DBD) plasma actuators with thin and complex geometry electrodes to exert instability control on two flow configurations whose dynamics are governed by primary and/or secondary instability mechanisms.The case of a three-dimensional boundary layer as encountered on a swept wing is studied using two forcing strategies to manipulate the transition induced by a stationary instability phenomenon. Here, an array of discrete roughness elements (DRE) is installed upstream of the DBD forcing in order to lock the origin and evolution of the stationary cross-flow (CF) vortices in the boundary layer. The first forcing approach is upstream flow deformation (UFD). The second approach based on direct modification of the base flow is also introduced (BFM). Independent of the forcing applied, a transition delay is observed. However, as the CF vortices are strongly amplified due to the use of DRE, the action by UFD approach can lead both to a direct attenuation of the CF vortices as envisaged but also to an unintentional action on the inflectional nature of the base flow. The BFM method results in a direct attenuation of the CF velocity component, which is also confirmed by a theoretical study of instability under the effect of the DBD actuator through a simplified model. This is not only the first experimental demonstration of transition delay on a swept wing using plasma actuators, but also the first experimental proof of concept of the BFM strategy.The wake of a plane mixed layer with a thick edge and the primary and secondary instability phenomena responsible for the spatio-temporal expansion of the wake are also studied. Frequency and then spatial forcing conditions are successively tested and analysed by spectral approach (spectral proper orthogonal decomposition, SPOD) on experimental data from multi-field time-resolved particle image velocimetry. The primary instability is excited by a spatially uniform forcing pulsed at the naturally most amplified frequency. It is shown that the mean component of the flow is not modified while the spectral content of the mixing layer is largely affected. This forcing leads, in particular, to the inhibition of the pairing of vortical structures due to the attenuation of sub-harmonic instabilities. Conversely, direct forcing of sub-harmonic instabilities results in a reinforcement of the pairing phenomena, leading to a higher growth rate of the mixing layer. Finally, spatially modulated forcing results in a growth that varies according to the spanwise position, which reflects both the reinforcement and the spatial modulation of large-scale spanwise structures. The modulation of the forcing according to the scale of the mixing layer always allows the modification of the spanwise structures but in addition, the coalescence of the streamwise and spanwise structures is favoured.The research work carried out confirms the ability of DBD plasma actuators to exert a forcing modulated both temporally and spatially. The proposed actuators allow only a partial control of the instability phenomena in the three-dimensional boundary layer while the high receptivity of the initial region of a mixing layer has led to significant results both on the dynamics of spanwise and streamwise coherent structures. Thanks to a large reduction of the electrical power consumed in the case of spatially modulated forcing, the efficiency of the control system is greatly improved

The present thesis is an experimental study of some aspects of unsteady two dimensional boundary layers subject to adverse pressure gradient. An adverse pressure gradient usually leads to boundary layer separation or an instability which may result in transition to turbulence. Unsteady boundary layer separation is not yet fully understood and there is no specific criterion proposed in literature for its occurrence. The details of separation depend on the Reynolds number, the geometry of the body (streamlined or bluff) and the type of imposed unsteady motion (impulsive, oscillatory etc.). Similarly there are many unknowns with respect to instability and transition in unsteady boundary layers, especially those having a streamwise variation. For unsteady flows it is useful to break up the pressure gradient term in the unsteady boundary layer equation into two components:(Formula) is the velocity at the edge of the boundary layer. The first term of the right hand side of this equation may be called the temporal component (Πt) which signifies acceleration or deceleration in time of the free stream and the second term is the spatial component (Πx) which represents the spatial or convective acceleration of the free stream. Many of the studies on instability in unsteady flows found in literature are carried out in straight tubes or channels, where the Πx term is absent. However, in many cases, especially in biological systems both terms are present. An example is the unsteady flow over the moving body of a fish. To study the effects of Πt and Πx on unsteady separation and instability we have built an unsteady water tunnel where the two components can be systematically varied. The flow is created by a controlled motion of a piston. By a suitable combination of the geometry of the model and the piston motion, different types of separation bubbles may be generated. In our studies the piston motion follows a trapezoidal variation: constant acceleration from rest, followed by constant velocity and then deceleration to zero velocity. We have chosen two geometries. One is a bluff body and thus has a high value of Πx and other is a small angle diffuser with a divergence angle 6.2° and thus having a small value of Πx. Upstream and downstream of the diffuser are long lengths of constant cross section. We have performed experiments with the above mentioned geometries placed in the tunnel test section. Flow is visualized using the laser induced fluorescence technique by injecting a thin layer of fluorescein dye on the test wall. Numerical simulations have been done using the software FLUENT. Boundary layer parameters like boundary layer, displacement and momentum thicknesses are calculated from the simulations and used to analyze the experimental results. For the flow in the diffuser, quasi-steady stability analysis of the instantaneous velocity profiles gives a general idea of stability behavior of the flow. Two types of experiments have been done with the bluff body. One is the unsteady boundary layer separation and the formation of the initial vortex for a flow that is uniformly accelerated from rest. We have found some scalings for the formation time (tv) of the separation vortex. The second type of experiment was to study the vortex shedding from the separating shear layer after the boundary layer has fully separated. At high enough Reynolds number shear layer vortices are seen to shed from the separation bubble. The Strouhal number based on the momentum thickness and the velocity at the edge of the boundary layer just upstream of the separation point is found to vary between 0.004 and 0.008. This value is close to the Strouhal number value of 0.0068 found in laminar separation bubbles on a flat plate. The second part of the study concerns with the evolution of the flow in the small angle diffuser with a mild variation of the spatial component of the pressure gradient. From the experimental visualizations we have found that the ratio of Πx and Πt at the start of the deceleration phase of the piston motion is an important parameter that determines the type of instability. This value of Πx/Πt is controlled by controlling the piston deceleration: a large deceleration gives a low Πx/Πt value and a low deceleration gives a large Πx/Πt value. Three types of instabilities have been observed in our experiments. In Type I, the first vortex forms at the maximum pressure gradient point (MPGP) and which grows disproportionately with time. However, instability vortices are seen later at other locations around the MPGP. In type II an array of vortices over a certain length are observed; the vortices grow with time. In Type III, which we observe for low decelerations, we observe initial vortices only in the diffuser section in the deceleration phase of the piston motion. Type III instability is similar to the one observed in dynamic stall experiments. In all cases the instability is very localized - it occurs only over some length of the boundary layer. Transition to turbulence, which is also localized, is observed at higher Reynolds numbers. The non-dimensional time for vortex formation is not very different from that found in straight channel experiments. Quasi-steady linear stability analyses for the boundary layer at the MPGP both for the top and the bottom walls show that the flow is absolutely unstable for some cases. In summary, the thesis looks at in a unified way the separation and instability of unsteady boundary layers with reverse flow. It is hoped that the results will be useful in predicting and understanding onset of separation and instability in practically occurring unsteady flows.

In this work, a DNS code was developed to investigate problems on transition in subsonic compressible boundary layer on a flat plate. Code validation tests were performed for linear and nonlinear stages of transition, on incompressible and compressible regimes. The focus of the present work is to investigate natural transition in subsonic boundary layers modeled by wave packets; and perform a preliminary study of transition induced by white noise. Three main problems were considered, namely, a DNS simulation and analysis of the ex- periment (MEDEIROS; GASTER, 1999b) of wave packet evolution on incompressible boundary layer, the influence of compressibility on wave packet evolution at subsonic Mach numbers and finally, a preliminary study of the evolution of a white noise perturbation in the boundary layer at Mach 0.2 and Mach 0.9. Comparisons between numerical and experimental results show remarkably good agreement in the linear and nonlinear stages, in both, spatial and Fourier spaces. A numerical simulation of this experiment and the analysis carried out is not available in the literature for wave packets in the incompressible boundary layer. The nonlinear modal analysis performed established the existence of tuned fundamental and subharmonic resonance of H-type and K-type in the packet. Influence of compressibility in the wave packet evolution was here investigated in boundary layers at Mach 0.7 and Mach 0.9. There are no works reported in the literature on wave packets in compressible subsonic boundary layer. In the linear regime, the oblique modes were the most unstable for Mach > 0.7, as expected by the results of the literature. In the nonlinear regime, strong streaks were observed, associated with low frequency modes that eventually decay downstream. An isolated wave packet at Mach 0.9 showed nonlinear amplification only in the subharmonic band, which may be associated to H-type or detuned resonance. However this packet has a relatively stable character. On the other hand, at Mach 0.9 spanwise interaction of wave packet pairs were more unstable than the isolated case, because stable modes for the isolated packet evolution becomes unstable in the wave packet interaction. This scenario evidenced the presence of oblique transition. Finally, the nonlinear evolution of the same white noise disturbance at Mach 0.2 and Mach 0.9 were observed to be completely different. In the incompressible boundary layer localized lambda vortex structures were observed, that could be associated to the local presence of H-type and/or K-type resonance. In the compressible regime, longitudinal vortex structures distributed across the entire domain seemed to be linked to oblique transition. In the white noise evolution, compressibility seems to have a stronger effect than in the wave packet evolution. In the conditions considered, the wave packet interaction appear to be a better representation of white noise compressible transition scenario.
No presente trabalho, um código DNS (Direct Numerical Simulation) foi desenvolvido para abordar problemas de transição para turbulência em camada limite subsônica compressível em uma placa plana. Foram realizados testes de validação de código , nos regimes linear e não linear do processo de transição, nos regimes incompressível e compressível. O foco do presente trabalho é estudar transição natural modelada por meio de pacotes de onda em camada limite compressível subsônica, e realizar uma análise preliminar da transição induzida por ruído branco. Três assuntos principais foram considerados: uma simulação DNS e uma análise comparativa com o experimento (MEDEIROS; GASTER, 1999b) sobre a evolução de um pacote de ondas em camada limite incompressível, a influência da compressibilidade na evolução de pacotes de ondas no regime subsônico, e por último, um estudo preliminar da transição induzida por ruído branco em Mach 0.2 e Mach 0.9. As comparações realizadas entre a solução numérica e os dados experimentais mostram uma boa concordância, nos regimes linear e não linear, tanto no espaço físico quanto no espaço de Fourier. A simulação numérica deste experimento e a análise realizada neste trabalho, não são encontradas na literatura para o regime incompressível. A análise modal não linear aplicada aos resultados, permitiu identificar a presença das ressonâncias tipo H e tipo K no pacote de ondas. A influência da compressibilidade na evolução dos pacotes de onda foi estudada em Mach 0.7 e Mach 0.9. Na literatura não há trabalhos sobre pacotes de ondas no regime sub- sônico. No regime linear da transição, os modos oblíquos resultam ser os mais instáveis para Mach > 0.7, como era de esperar, de acordo com os resultados da literatura. No regime não linear, foram observadas estrias de moderada amplitude, associadas com modos de baixa frequência que acabam decaindo. O pacote de ondas em Mach 0.9 apresentou amplificação não linear somente na banda subharmônica, que pode ser associada com transição tipo H ou ressonância dessintonizada. No entanto, o comportamento geral neste regime é estabilizante. Por sua vez, a interação entre pacotes de ondas em Mach 0.9 mostrou um comportamento desestabilizante, pois a interação acaba gerando amplificação não linear em modos que decaem no pacote isolado. Os modos amplificados sugerem a presença do mecanismo de transição oblíqua. Finalmente, a evolução da mesma perturbação constituída por ruído branco em Mach 0.2 e Mach 0.9, resultaram ser completamente diferentes. Na camada limite incompressível foram observados vórtices tipo lambda, que poderiam ser gerados pela presença localizada das ressonâncias tipo H e/ou tipo K. No regime compressível foram observados vórtices distribuidos em todo o domínio, o que sugere a presença da transição oblíqua. Na transição gerada por ruído branco a compressibilidade teve uma influência maior que no pacote de ondas. Nas condições estudadas, a interação entre pacotes de ondas parece ser uma melhor representação do ruído branco no regime compressível.

Etude en canal hydrodynamique de processus de formation des rouleaux de goertler pres du seuil d'instabilite. Visualisation par fluorescence induite par laser et mesure du champ de vitese par anemometrie laser doppler. On identifie trois instabilites secondaires et on propose un modele simple decrivant la premiere

Ce travail de thèse expérimental étudie les instabilités et la transition de la couche limite produite par un disque en rotation. Pour l’écoulement naturel (c.-à-d. sans forçage extérieur), les mesures des profils de vitesse moyenne, de spectres en fréquence et de moyennes de phase des séries temporelles de vitesse ont permis de distinguer différents régimes en fonction de la distance adimensionnelle R à l’axe du disque. Pour les faibles valeurs de R, les profils de vitesse moyenne suivent la solution de von Kármán. Pour des valeurs plus importantes de R, des écarts à cette solution analytique sont observés et augmentent avec R. Ces écarts sont dus à la croissance spatiale de modes instables de la couche limite (vortex .cross-flow.), et la mesure du taux de croissance spatiale de ces modes correspond bien aux prédictions théoriques de l’analyse de stabilité linéaire. Dans cet écoulement, la transition se produit vers R ≈ 530 et la turbulence pleinement développée s’installe vers R ≈ 600. Les profils dans la région pleinement turbulente suivent la loi logarithmique des couches limites turbulentes et les spectres de vitesse présentent une loi en puissance de type Kolmogorov. Pour étudier la réponse au forçage, un dispositif expérimental a été mis au point qui permet d’exciter des perturbations stationnaires (dans le référentiel du laboratoire) ou en rotation à une fréquence qui peut être réglée indépendamment de la fréquence de rotation du disque. La réponse de l’écoulement à ces deux types de forçage et avec deux formes différentes pour l’élément de forçage a été étudiée. Un forçage stationnaire produit un sillage qui décroît avec la distance à l’élément de forçage, en accord avec la théorie. Le forçage avec des éléments en rotation peut produire un paquet d’ondes amplifié qui, bien que non linéaire, suit des trajectoires proches de celles prédites par la théorie linéaire
This dissertation concerns experimental work on the instability and transition of the rotating-disk boundary-layer flow. In the case of the natural flow (i.e. without forcing), measurements of mean-flow profiles, frequency spectra and phase-locked averages of the velocity time series allow us to distinguish different flow regimes as a function of nondimensional distance, R, from the disk axis. As R increases, the mean-velocity profiles initially follow the von Kármán solution. At higher R, departures arise and increase with R. These departures are due to the spatial growth of boundary-layer instability modes (cross-flow vortices), whose radial growth rates are found to match linear-theory predictions. The flow becomes transitional at R ≈ 530 and fully turbulent by R ≈ 600. The profiles in the fully turbulent region follow the log law of turbulent boundary layers and the velocity spectra exhibit Kolmogorov-type power laws. To study the response to forcing, an experimental apparatus has been designed which allows the excitation of stationary (in thelaboratory frame of reference) disturbances or disturbances which rotate with a frequency which can be varied independently of the disk rotation rate. The flow response to both types of forcing and two forcing-element geometries was studied. Stationary forcing produces a wake which decays with distance from the element, in agreement with theory. Forcing due to rotating elements can generate growing wavepacket-like disturbances, which although nonlinear, follow trajectories close to linear-theory predictions

La dynamique d'instabilité d'un écoulement laminaire décollé est étudiée expérimentalement et son contrôle par le biais de la simulation numérique. La configuration étudiée est une couche limite laminaire décollée au dessus d'une géométrie de type bosse.Pour une certaine gamme de paramètres, l'écoulement de recirculation en aval de la bosse est caractérisé par un battement basse fréquence. L'étude expérimentale de cette dynamique a permis de retrouver les différents régimes d'instabilité mis a jour par voie numérique. Ces résultats prouvent notamment que les instabilités basse fréquence, dont l'existence a été surtout mise en évidence dans des configurations d'écoulements compressibles, sont un phénomène générique pour des bulles de recirculations allongées. Le contrôle du battement basse fréquence est ensuite étudié par voie numérique suivant deux approches complémentaires. Un asservissement en boucle fermée de la dynamique de perturbation linéaire est tout d'abord proposé. Les modes d'instabilité linéaires sont utilisés afin de construire des modèles réduits de la dynamique de perturbation. Cette réduction de modèle donne lieu à des estimateurs de faible dimension capables d'estimer la dynamique et de la contrôler. Ainsi la dynamique d'instabilité linéaire peut être supprimée en couplant le système de Navier-Stokes linéarisé avec le contrôleur.Le contrôle de la dynamique non linéaire est ensuite étudié en utilisant une méthode d'optimisation Lagrangienne. Cette méthode permet de calculer les lois de contrôle à partir de la dynamique non linéaire des équations de Navier-Stokes
The dynamics and control of a separated boundary-layer flow have been investigated. Separation is triggered by a bump mounted on a flat plate and the transition dynamics has been investigated experimentally. For a certain parameter range, the recirculation region is subject to self-sustained low-frequency oscillations, and results from the numerical simulation for the same geometry are recovered. These results show that low frequency oscillations, observed mainly in compressible flow regimes, are inherent to elongated recirculation bubbles.The control of this low-frequency instability has been investigated using modern control theory based on two complementary approaches. Feedback control of the linear perturbation dynamics is first considered. Global instability modes are used to build reduced-order estimators. This model reduction gives rise to low-dimensional compensators capable of controlling the unstable dynamics. Once coupled to the unstable linearised Navier-Stokes system, the compensator is seen to succesfully control the unstable dynamics. The control of the nonlinear dynamics is then investigated using adjoint-based optimisation procedures. This method is used to compute control laws based on a complete knowledge of the nonlinear dynamics. Although the low-frequency instability is clearly attenuated, it seems difficult to control the flow towards its steady state, using only a few blowing/suction actuators localized on the wall

Ce travail de thèse expérimental étudie les instabilités et la transition de la couche limite produite par un disque en rotation. Pour l'écoulement naturel (c.-à-d. sans forçage extérieur), les mesures des profils de vitesse moyenne, de spectres en fréquence et de moyennes de phase des séries temporelles de vitesse ont permis de distinguer différents régimes en fonction de la distance adimensionnelle R à l'axe du disque. Pour les faibles valeurs de R, les profils de vitesse moyenne suivent la solution de von Kármán. Pour des valeurs plus importantes de R, des écarts à cette solution analytique sont observés et augmentent avec R. Ces écarts sont dus à la croissance spatiale de modes instables de la couche limite (vortex .cross-flow.), et la mesure du taux de croissance spatiale de ces modes correspond bien aux prédictions théoriques de l'analyse de stabilité linéaire. Dans cet écoulement, la transition se produit vers R ≈ 530 et la turbulence pleinement développée s'installe vers R ≈ 600. Les profils dans la région pleinement turbulente suivent la loi logarithmique des couches limites turbulentes et les spectres de vitesse présentent une loi en puissance de type Kolmogorov. Pour étudier la réponse au forçage, un dispositif expérimental a été mis au point qui permet d'exciter des perturbations stationnaires (dans le référentiel du laboratoire) ou en rotation à une fréquence qui peut être réglée indépendamment de la fréquence de rotation du disque. La réponse de l'écoulement à ces deux types de forçage et avec deux formes différentes pour l'élément de forçage a été étudiée. Un forçage stationnaire produit un sillage qui décroît avec la distance à l'élément de forçage, en accord avec la théorie. Le forçage avec des éléments en rotation peut produire un paquet d'ondes amplifié qui, bien que non linéaire, suit des trajectoires proches de celles prédites par la théorie linéaire.

Ces travaux de recherche portent sur la caractérisation des phénomènes instationnaires associés aux écoulements décollés induits à la fois par un gradient de pression adverse et un effet de courbure. Ce type de décollement est très couramment rencontré, en particulier dans le secteur des transports. Cette étude repose sur une approche purement expérimentale réalisée en canal hydrodynamique à l’aide de techniques de mesure non intrusives permettant de ne pas dénaturer la dynamique très sensible du phénomène de décollement de couche limite. Le décollement est, dans notre cas de figure, provoqué par un obstacle 2dne présentant pas de rupture de pente. Le régime d’écoulement étudié est principalement turbulent et la gamme des nombres de Kármán analysée s’étale de 60 à 730. L’objectif principal de cette étude est d’évaluer les effets Reynolds sur l’étendue et l’existence même du phénomène de décollement de couche limite, mais également sur la dynamique des instabilités, identifiées à plus bas régime dans la littérature. Les mesures effectuées dans le cadre de ces travaux ont tout d’abord permis de constituer une base de donnéesexpérimentale étoffée, et d’établir que le décollement de couche limite ainsi que les instabilités induites par celui-ci, identifiées en régime laminaire, persistent à plus haut nombre de Kármán. Les fréquences associées aux instabilités ont également été identifiées ainsi que les paramètres caractéristiques pilotant leur dynamique. La dynamique spatio-temporelle de ces instabilités et en particulier celle du phénomène debattement du bulbe décollé a été détaillée notamment par le biais d’une analyse stochastique. Finalement, la répartition relativement étendue des grandes échelles tourbillonnaires associées aux mécanismes instables (soulignée notamment par leur émergence spectrale large bande) a également été mise en évidence, ainsi que certains phénomènes dynamiques secondaires. L’ensemble de ces résultats et en particulier l’identification des paramètres clés pilotant la dynamique du décollement de la couche limite s’avèreront très utiles en vue de concevoir par la suite des modèles simplifiés reproduisant le plus fidèlement possible la dynamique des décollements afin de mieux pouvoir les contrôler
These investigations concern the characterization of unsteady phenomena associated to the boundary layer separation induced by both an adverse pressure gradient and a curvature effects. This kind of separation is very usual, particularly in the transport field. This study, essentially based on an experimental approach, is carried out in an hydrodynamic channel using non intrusive measurement techniques. They respect the very sensitive dynamics of the boundary layer separation phenomenon. The separation is, in our case, induced by a 2d obstacle without sharp corner. The studied flow regime is mainly turbulentand the analyzed Kármán number ranges from 60 to 730. The main aim of this study is to estimate the Reynolds number effects on the boundary layer separation length and even on the existence of such phenomenon, but also on the instabilities dynamics, identified in the literature especially for laminar flow regime. The measurements made within the framework of these works allowed, first to built a large experimental database, and secondly to establish that the boundary layer separation and also the associate instabilities, identified for laminar flow, persist even for higher Kármán number. The frequencies associated to the instabilities phenomena have been also identified as well as the characteristic parameters driving their dynamics. The instabilities space-time dynamic, in particular those of the flapping phenomenon were detailed using stochastic analysis. Finally, the large scales distribution associated with the unstable mechanisms (underlined by their spectral broadband frequency range) were also highlighted, as well asothers secondary dynamic phenomena. All these results, especially the identification of the key parameters driving the boundary layer separation, will turn out very useful to design afterward simplified models reproducing as faithfully as possible the separation dynamics and to be able to control them better

The transition from a laminar to a turbulent flow strongly modifies the boundary layer properties.Understanding the mechanisms leading to transition is crucial to reliably predict aerodynamicperformances. For boundary layers subjected to high levels of external disturbances, the naturaltransition due to the amplification of the least stable mode is replaced by an early transition, calledBypass transition. This is the result of non-normal mode interactions that lead to a phenomenon oftransient growth of disturbances. These disturbances are known as Klebanoff modes and take theform of streamwise velocity streaks.This thesis aims at understanding this linear mechanism of transient growth and quantifying itsinfluence on the classical modal amplification of disturbances. This is done by computing theso-called optimal perturbations, i.e. the initial disturbances that undergo maximum amplificationin the boundary layer.These optimal perturbations are first determined for two-dimensional compressible boundary layersdeveloping over curved surfaces. In particular, we show that Klebanoff modes naturally evolvetowards Görtler vortices that occur over concave walls. Three-dimensional boundary layers arethen considered. In such configurations, transient growth provides an initial amplitude to crossflowvortices. Finally, applying the tools developed in this thesis to new flow cases such as swept wingsprovides further understanding of the phenomenon of transient growth for realistic geometries
Le passage du régime laminaire au régime turbulent s’accompagne d’importantes modifications despropriétés physiques de la couche limite. La détermination précise de la transition est donc crucialedans de nombreux cas pratiques. Lorsque la couche limite se développe dans un environnementextérieur faiblement perturbé, la transition est gouvernée par l’amplification du mode propre le moinsstable. Lorsque l’intensité des perturbations extérieures augmente, des interactions multimodalesentraînent une amplification transitoire des perturbations. Ce phénomène peut conduire à unetransition prématurée, appelée transition Bypass. Les perturbations prennent alors la forme destries longitudinales de vitesse appelées modes de Klebanoff.L’objectif de cette thèse est d’étudier ce mécanisme linéaire de croissance transitoire et soninfluence sur l’amplification modale classique des perturbations. Cela passe par la déterminationdes perturbations les plus amplifiées au sein de la couche limite, appelées perturbations optimales.Ces perturbations optimales sont d’abord calculées pour des couches limites bidimensionnelles etcompressibles se développant sur des surfaces courbes. En particulier, on montre que les modes deKlebanoff évoluent vers les tourbillons de Görtler qui se forment sur des parois concaves. Le cas plusgénéral de couches limites tridimensionnelles est ensuite envisagé. Pour de telles configurations, lacroissance transitoire fournit une amplitude initiale aux instabilités transversales. Enfin, l’applicationdes outils développés dans cette thèse fournit de nouveaux résultats pour des cas d’écoulementsautour de géométries réalistes comme une aile en flèche

Le bruit de cavité est un phénomène très fréquent dans le domaine des transports aériens.Il survient notamment lors de l'approche à l'atterrissage, où des interactions entre la cellule de l'aéronef et l'écoulement sont à l'origine de fortes émissions tonales. Il devient dès lors une source de pollution acoustique non-négligeable pour les populations résidant à proximité de zones aéroportuaires. Les études numériques et expérimentales décrites jusqu'à présent dans la littérature abordent essentiellement le cas des cavités rectangulaires. Pourtant, les cavités rencontrées en pratique dans l'industrie aéronautique impliquent des géométries souvent plus complexes. Lorsque ces cavités sont soumises à une excitation de nature aérodynamique, leur spécificité géométrique conduit le plus souvent à des réponses acoustiques assez éloignées des estimations issues de modèles académiques construits sur l'observation de cavités rectangulaires. Quelques travaux seulement abordent le cas des cavités cylindriques.Ce travail est consacré à l'étude aéroacoustique des cavités cylindriques, à l'initiative d'Airbus. Il s'inscrit dans le cadre du projet AEROCAV soutenu par la Fondation de Recherche pour l'Aéronautique & l'espace (FRAE). Son objectif est de déterminer les mécanismes impliqués dans les émissions acoustiques intenses et tonales pour les configurations étudiées.Une première partie présente les résultats expérimentaux issus des campagnes de mesures menées dans la soufflerie anéchoïque du Centre Acoustique du LMFA et de l'école Centrale de Lyon. Un modèle semi-empirique, reposant sur l'hypothèse d'une résonance acoustique pilotée par les instabilités présentes dans la couche de cisaillement à l'ouverture de la cavité,est construit à partir du modèle d'Elder (1978). Le modèle permet d'estimer les fréquences susceptibles de dominer l'acoustique rayonnée en champ lointain à partir de la donnée du champ moyen de vitesse longitudinale, que l'on mesure dans le plan de l'écoulement par Vélocimétrie par Imagerie des Particules (PIV).Une seconde partie est destinée au calcul direct du bruit rayonné par un écoulement laminaire ou turbulent affleurant une cavité cylindrique de référence. Il consiste à calculer le champ acoustique directement à partir de la résolution des équations tridimensionnelles de la mécanique des fluides. Le solver Alesia est présenté dans une version modifiée et adaptée à la mise en oeuvre d'une approche multidomaine d'ordre élevé faisant intervenir plusieurs maillages se recouvrant. Des techniques d'interpolation sont spécifiquement développées en vue d'assurer une communication bidirectionnelle entre les différents maillages, malgré des contraintes géométriques fortes. Un modèle d'excitation de l'écoulement est aussi développé afin de disposer de fluctuations dans l'écoulement incident, pour le cas turbulent. Ces deux points font l'originalité des calculs réalisés.Les simulations, menées sur une cavité de rapport d'aspect géométrique égal à 1 et soumise à un écoulement incident à Mach 0.2, montrent que le rayonnement acoustique peut être fidèlement reproduit numériquement. La couche de cisaillement est caractérisée par la présence de deux larges structures tourbillonnaires s'amplifiant lors de leur convection. Leur présence s'accompagne de fortes fluctuations de vitesse à l'origine d'un débit aérodynamique de fluide à l'ouverture qui excite la cavité acoustiquement. Une résonance forcée s'établit dans celle-ci, excitant la couche de mélange au voisinage du point de séparation. Ce couplage auto-entretenu est à l'origine du rayonnement acoustique intense et fortement tonal de la cavité. Il s'établit à une fréquence proche de la fréquence prédite par le modèle semi-empirique développé.

With novel application of optical techniques, the slender-body hypervelocity boundary-layer instability is characterized in the previously unexplored regime where thermo-chemical effects are important. Narrowband disturbances (500-3000 kHz) are measured in boundary layers with edge velocities of up to 5~km/s at two points along the generator of a 5 degree half angle cone. Experimental amplification factor spectra are presented. Linear stability and PSE analysis is performed, with fair prediction of the frequency content of the disturbances; however, the analysis over-predicts the amplification of disturbances. The results of this work have two key implications: 1) the acoustic instability is present and may be studied in a large-scale hypervelocity reflected-shock tunnel, and 2) the new data set provides a new basis on which the instability can be studied.

The laminar-to-turbulent transition process in swept-wing boundary layers is often dominated by an inflectional instability arising from crossflow. It is now known that freestream turbulence and surface roughness are two of the key disturbance sources in the crossflow instability problem. Recent experimental findings have suggested that freestream turbulence of low intensity (less than 0.2%) may have a larger influence on crossflow instability than was previously thought. The present work involves experimental measurement of stationary and traveling crossflow mode amplitudes in freestream turbulence levels between 0.02% and 0.2%. A 1.83 m chord, 45-degree swept-wing model is used in the Klebanoff-Saric Wind Tunnel to perform these experiments. The turbulence intensity and length scales are documented. Although a significant amount of research on the role of turbulence has been completed at higher turbulence levels, comparatively little has been done at the low levels of the present experiments, which more closely reflect the flight environment. It is found that growth of the traveling crossflow mode is highly dependent on small changes to the freestream turbulence. Additionally, previously studied attenuation of saturated stationary disturbance amplitudes is observed at these low turbulence levels. The extent of laminar flow is also observed to decrease in moderate freestream turbulence.

An experimental study of both the weakly non-linear as well as the three-dimensional nature of boundary layer transition is conducted using the active surface heating technique of Liepmann et al. In the present study, this technique is extended to provide a means for controllably and repeatably introducing three-dimensional disturbances into a laminar boundary layer. A review of the surface heating technique is presented along with a discussion of some peculiarities encountered in extending this technique to three-dimensional geometries. A thorough description of the design and operation of a programmable 32-element heater array and the supporting instrumentation are given as well.

The heater array is first used to study the effect of weak nonlinearity on boundary layer transition. By keeping the forced disturbances as two-dimensional as possible, it is shown that the effects of weak non-linearity are relatively benign. The growth rates are seen to follow the linear theory up to perturbation amplitudes (τ'_wτ̅_w) of nearly twelve percent. The only deviation from the linear theory arises in the form of non-linearly generated harmonics phase-locked to the fundamental. It is concluded that although these non-linearly generated harmonics do alter the wave behavior to some extent, they are by themselves not sufficient to explain the transition from small linear oscillations to the large amplitude, broad-band, three-dimensional oscillations characteristic of a fully turbulent boundary layer.

The effect of three-dimensionality on boundary layer transition is then investigated through an analytical and experimental study of single oblique instability waves. This subject has remained largely unexplored, as such disturbances were generally thought to be more stable and therefore less dangerous than their two-dimensional counterparts. Through a series of experiments, however, it is shown that certain conditions exist for which oblique waves are observed to be more unstable than any two-dimensional wave. It is shown that oblique waves exhibit a non-stationary period-doubling behavior that is not seen in two-dimensional disturbances. A vortex pairing mechanism is proposed to explain this behavior, and is shown to occur in a manner consistent with the Biot-Savart law for the induced velocity field.

This dissertation analyzes the effect of periodic roughness elements on the stability of a flat plate boundary layer. Receptivity data is extracted from direct numerical simulations and experimental data and the results are compared to theoretical predictions. This analysis shows that flow in the immediate vicinity of roughness elements is non-linear; however, the evolution of roughness-induced perturbations is a linear phenomena. New techniques are developed to calculate receptivity information for cases where direct numerical simulations are not yet possible. Additionally, the stability behavior of the roughness wake is analyzed. New instability modes are found, and the effect of boundary layer complexity, perturbation amplitude and other factors are examined. It is shown that the wake is much less stable than optimal perturbation theory predicts, and highlights the importance of receptivity studies. The implication of these results on transition-to-turbulence is discussed, and future work is proposed. T

This research focuses on measurements of a convective shear-layer instability seen naturally in quiet hypersonic flow. Experiments were carried out in the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University. The BAM6QT provides low-disturbance hypersonic flow with freestream noise levels similar to what would be experienced by a flight vehicle. To obtain high-speed, off-the-surface measurements of the instability, a modified focused laser differential interferometer (FLDI) was first designed to work with the contoured Plexiglas windows available in the tunnel.

Boundary layer rolls are a rather frequent phenomena, where regions of alternating up- and downdraft motion causes clouds to form in elongated, parallel rows oriented with the mean wind direction. The clouds can be seen during certain atmospheric conditions and are often called ”cloud streets” because of their characteristic appearance. By performing a linear instability analysis, the underlying mechanisms causing the onset of boundary layer rolls has been analysed in this study. There are two governing mech- anisms that cause the boundary layer rolls to form, the thermal instability and the dynamic instability. The thermal instability is caused by convection in an unstable airmass, while the dynamic instability usually is associated with neutral or stable conditions. The dynamic instability arise due to an inflection point in the wind profile, around which eddies develop. In a previous study by Svensson et al. (2017), rolls were observed over the Swedish east-coast, stretching out over sea during four days; 2 of May 1997, 3 of May 1997, 17 of May 2011 and 25 of May 2011. The aim of this study is to simulate the rolls on these four dates, analyse the underlying mechanisms and establish what type of instability that primarily causes the rolls to form. The linear stability analysis performed in this study indicate that the dynamic instability is the main mechanism giving rise to the rolls on all four studied dates. The rolls are found to arise over the Swedish mainland and are advected out over the sea. Both the orientation of the rolls and the modeled wind direction are in accordance with the observations. A qualitative agreement is found for the wavelength, the amplitude and the altitude of the rolls, when comparing the results of this study with the observations.