Heat transfer augmentation is of paramount importance in energy transfer and storage systems and the idea of using the inherent vibrations in a system to enhance heat transfer needs to be thoroughly researched upon. The current study numerically investigates an infinitesimally thin plate-fin undergoing forced oscillations over a range of amplitudes and frequencies in the presence of an approach flow. Reduced frequencies of 0.25 ≤ k ≤16 and plunge amplitudes of 0.03125 ≤ h ≤ 8 are investigated at Re=100 and Pr = 0.71. It is shown that the combined effect of frequency and amplitude on heat transfer enhancement can be accounted for as a single parameter “plunge velocity” (0.25 ≤ kh ≤ 4) instead of the individual frequency and amplitude values. For kh > 0.5 a significant increase in Nusselt number ( is observed compared to a stationary plate. With increasing kh or more vigorous oscillations, the increase in becomes more prominent and similar trends and comparable magnitudes were observed for a constant value. Unlike the hydrodynamic counterpart of the study, both Leading Edge Vortices (LEVs) and Trailing Edge Vortices (TEVs) are found to act positively to induce enhanced heat transfer on the plate. Finally, the dependence of heat transfer augmentation on the frequency and amplitude of vibration is quantified with a simple parameterization for a plate-fin in a fluid medium. / M.S. / Heat transfer enhancement is of paramount importance in energy transfer and storage systems. The idea of using the inherent mechanical vibrations in a heat producing system to enhance transfer of unwanted heat from that system needs to be thoroughly researched upon. To investigate this idea, we numerically study an infinitesimally thin plate-fin undergoing forced oscillations over a range of amplitudes and frequencies in the presence of an incoming air flow. It is shown that the combined effect of frequency and amplitude on heat transfer enhancement can be accounted for as a single parameter called “plunge velocity” instead of the individual frequency and amplitude values. For a significant plunge velocity, a significant increase in Nusselt number ( is observed compared to a stationary plate representing an increase in the extent of heat transferred. With more vigorous oscillations, the increase in becomes more prominent and similar trends and comparable magnitudes were observed for a constant value. Finally, the dependence of heat transfer augmentation on the frequency and amplitude of vibration is quantified with a simple parameterization for a plate-fin in a fluid medium.

There have been very few studies investigating the rough wall pressure spectra under fully rough flows, which are relevant to many common engineering applications operating within this regime. This investigation uses the Virginia Tech Stability Wind Tunnel to perform experiments on a series of high Reynolds number zero pressure gradient turbulent boundary layers formed over rough walls in an effort to better understand and characterize the behavior of the rough wall pressure spectrum. The boundary layers were fully rough, and the boundary layer height remained sufficiently larger than the height of the roughness elements. Two rough surfaces were tested. One consisted of an array of 1-mm ordered hemispherical elements spaced 5.5-mm apart, and the other contained 3-mm hemispherical elements randomly spaced, but with the same element density as 1/3 of the 1-mm ordered roughness. The wall pressure spectrum and its scaling were then studied in detail, and it was found that the rough wall turbulent pressure spectrum at vehicle relevant conditions is defined by three scaling regions. One of which is a newly discovered high frequency scaling defined by viscosity, but controlled by the friction velocity adjusted to exclude the pressure drag on the roughness elements. Based on these three scaling regions an empirical model describing the wall pressure spectra for hydraulically smooth, traditionally rough, and fully rough flows was explored. Two point wall pressure fluctuations were also analyzed for each surface condition, and it was found that the roughness inhibits the convective velocities within the inner portions of the boundary layer. / Master of Science

The history and trajectory of the human race is inseparable from our innate need to explore the unknown. As human exploration drives boundless new insights into the universe, characterization and accurate modeling methods are required to develop the next generation of exploratory vehicles to map and analyze foreign lands. As such the presented work looks to provide characterization and modeling approaches for unsteady aerodynamic phenomena in the extraterrestrial environments of Mars and Titan. Specifically, unsteady aerodynamic loads including dynamic stall are characterized using high-fidelity numerical experiments to better understand the effects of low Reynolds number and high Mach number flows on the process. Additionally, modeling of unsteady aerodynamic behavior at low Reynolds numbers similar to those observed when designing the Mars ingenuity rotorcraft are developed and extensively evaluated. Lastly, the characterization and multi-fidelity modeling of unsteady aerodynamic effects under Titan atmospheric conditions is conducted for a coaxial rotor system.

Experimental investigations were conducted with and without the presence of the surface-mounted obstacle to quantify its effects on the far wake. The obstacle chosen for this study was a 3:2 elliptical nose NACA 0020 tail wing-body (Rood body), approximately of height equal to the boundary layer thickness at one of the measurement locations of the flow. The experiments were performed by varying the Reynolds number of the flow and manipulating the pressure gradient distributions using a NACA 0012 airfoil placed within the wind tunnel test section. The measurements were acquired utilizing a spanwise traversing boundary layer rake and a point pressure sensing microphone array. The findings reveal that the presence of the obstacle introduces disruptions in the flow, such as vortex and jet regions in the wake. However, the overall flow behavior remains consistent with that of an undisturbed turbulent boundary layer, for varying Reynolds numbers and pressure gradients. Notably, an adverse pressure gradient and lower Reynolds number both accentuate the prominence of the jet and vortex region within the wake, with the trend reversing towards the other end of the spectrum. This behavior is akin to the larger turbulent boundary layer under adverse pressure gradients and lower Reynolds numbers. Furthermore, the presence of obstacles induces an increase in the overall level of the wall pressure spectrum by approximately 2 dB, regardless of the flow condition. Additionally, it leads to a deviation in the slope of the mid-frequency range of the autospectra compared to the smooth wall case. Specifically, the mid-slope frequency of an undisturbed turbulent boundary layer is steeper than that observed in the disturbed wake flow caused by the obstacle. / Master of Science / The interaction between turbulence and aerodynamic surfaces gives rise to wall-pressure fluctuations, which in turn induce structural vibrations and acoustic noise. On surfaces turbulent flows meet, antennae, flaps, and other frequently mounted measuring devices. The flow in their wake is impacted by the coherence of a turbulent boundary layer being disrupted by these impediments mounted on aerodynamic surfaces. They also alter the nature of the pressure fluctuations that are generated on the surface of interest. The far wake of a Rood Body obstacle was studied using a point pressure sensing microphone array and a spanwise traversing boundary layer rake. Experimental measurements were taken for a range of Reynolds numbers and pressure gradient environments at the Virginia Tech Stability Wind Tunnel. Results show that the boundary layer rake measurements resolve the presence of the obstacle wake successfully, by characterizing the wake structures and confirming the presence of jet and vortex regions in the wake of the obstacle. Surface pressure measurements reveal that the presence of the obstacle causes the low-frequency content of the wall pressure to be less dominant than the no obstacle case, while the high-frequency content becomes more dominant in the presence of the obstacle. The presence of obstacles also increases the overall levels of the wall pressure spectrum by approximately 2 dB.

Three different models, relating to the study of microswimmers immersed in a low Reynolds number fluid, are presented. The underlying, mathematical concepts employed in each are developed using singularity methods of Stokes flow. The first topic concerns the motility of an artificial, three-sphere microswimmer with prescribed, non-reciprocal, internal forces. The swimmer progresses through a low Reynolds number, nonlinear, viscoelastic medium. The model developed illustrates that the presence of the viscoelastic rheology, when compared to a Newtonian environment, increases both the net displacement and swimming efficiency of the microswimmer. The second area concerns biological microswimming, modelling a sperm cell with a hyperactive waveform (vigorous, asymmetric beating), bound to the epithelial walls of the female, reproductive tract. Using resistive-force theory, the model concludes that, for certain regions in parameter space, hyperactivated sperm cells can induce mechanical forces that pull the cell away from the wall binding. This appears to occur via the regulation of the beat amplitude, wavenumber and beat asymmetry. The next topic presents a novel generalisation of slender-body theory that is capable of calculating the approximate flow field around a long, thin, slender body with circular cross sections that vary arbitrarily in radius along a curvilinear centre-line. New, permissible, slender-body shapes include a tapered flagellum and those with ribbed, wave-like structures. Finally, the detailed analytics of the generalised, slender-body theory are exploited to develop a numerical implementation capable of simulating a wider range of slender-body geometries compared to previous studies in the field.

Cette thèse traite de la dynamique de cellules sanguines dans la microcirculation. Cette appellation regroupe les deux thématiques de mon travail. La première est l'étude du mouvement de globules rouges soumis à un écoulement de cisaillement. Prenant la suite des travaux réalisés par Manouk Abkarian, Magalie Faivre et Annie Viallat, nous avons étudié le mouvement de cellules dans un flux oscillant et mis en évidence l'apparition de chaos (Dupire J. et al, PRL 104,168101 (2010)). Nous avons ensuite repris l'étude sous écoulement constant pour comprendre les régimes de mouvement encore non étudiés (article accepté à PNAS). Tous ces travaux se basent sur un modèle à forme ellipsoïdale constante (type Keller & Skalak) auquel a été rajouté un terme tenant compte de l'élasticité de la membrane. Pour mieux modéliser la mémoire de forme, nous avons recalculé les équations du modèle en tenant compte d'une nouvelle forme non contrainte du cytosquelette élastique. Elle nous permet entre autres d'ajuster le modèle aux données expérimentales en utilisant des valeurs de viscosité et de module élastique de cisaillement compatibles avec la littérature. Le deuxième partie traite de l'étude du mouvement de globules blancs dans un réseau de canaux microfluidiques. Ce réseau est régulier et possède des dimensions biomimétiques. Nous étudions comment la rhéologie des cellules influe sur leur mouvement à travers le dispositif. Nous montrons que l'entrée des cellules, et donc leur première déformation, peut être utilisée pour obtenir des informations sur leur rhéologie (viscosité, élasticité, tension). / This thesis deals with dynamics of blood cells in microflow. This title regroups two aspects of my work. The first one studies the movement of red blood cells (RBC) under flow. Continuing the work done by M. Abkarian, M. Faivre and A. Viallat, we looked at RBCs in an oscillating shear flow and showed the presence of chaos in the motion (Dupire J. et al, PRL 104,168101 (2010) ). Then we continued the study of RBC under constant flow to understand the regime of motion that were still to elucidate (PNAS, accepted for publication). These works use a ellipsoidal fixed shape model (based on Keller and Skalak's) to which we add an elastic membrane term. To take into account the shape memory, we calculated again the equations of motion considering a new stress-free shape of the elastic cytoskeleton. It allows us to fit the model on the experimental data using viscosity and elasticity coefficient compatible with the litterature. The second part deals with the motion of white blood cell (WBC) in a microfluidic channel network. The device has a regular geometry and has biomimetic shape characteristics matching the human lung mean values. We aim to study how the cell's rheology is related to their motion through the device. We show how the entry of the cell, and thus their first deformation, can be used to obtain information about a single cell rheology (viscosity, elasticity, tension). The motion is then decomposed in 2 phases : a transient regime right after the entrance and a final stationary regime. We study these regimes in terms of cellular deformation and wall friction.

Flow Structure and fluid transport via advection around pectoral fin of larval ZebraFish are studied numerically using Immersed Boundary Method, Lagrangian Coherent Structure, passive particle tracing, vortex core evolution and four statistically defined mixing numbers. Experimental fish kinematics for nominal swimming case are obtained from previous researchers and numerically manipulated to analyze the role of different body motion kinematics, Reynolds number and fin morphology on flow structure and transport. Hyperbolic strain field and vortex cores are found to be effective particle transporter and their relative strength are driving force of varying flow structure and fluid transport. Translation and lateral undulation of fish; as a combination or individual entity, has coherent advantages and drawbacks significant enough to alter the nature of fluid advection. Reynolds number increase enhances overall fluid transport and mixing in varying order for different kinematics and nominal bending position of fin has average transport capability of other artificially induced fin morphology. / Includes bibliography. / Thesis (M.S.)--Florida Atlantic University, 2016. / FAU Electronic Theses and Dissertations Collection

Submitted by Fabricia Fialho Reginato (fabriciar) on 2015-08-27T23:08:49Z No. of bitstreams: 1 MarcosWOYCIEKOSKI.pdf: 2220255 bytes, checksum: 001c865faf4b29be82c72c3341fa51a4 (MD5) / Made available in DSpace on 2015-08-27T23:08:49Z (GMT). No. of bitstreams: 1 MarcosWOYCIEKOSKI.pdf: 2220255 bytes, checksum: 001c865faf4b29be82c72c3341fa51a4 (MD5) Previous issue date: 2012-03 / CAPES - Coordenação de Aperfeiçoamento de Pessoal de Nível Superior / Com a rápida evolução da tecnologia, os dispositivos eletrônicos tornaram-se compactos e com o alto poder de processamento, aumentando a geração de calor. Mas devido à baixa eficiência de ventiladores e dissipadores utilizados atualmente, há a necessidade de desenvolver novas formas de resfriamento. O uso de jatos sintéticos no resfriamento de dispositivos eletrônicos ainda é incipiente. Estudos monstram que este método pode ser uma alternativa eficaz. Assim, neste trabalho foi desenvolvido um estudo experimental com jatos sintéticos onde foram analisadas diferentes configurações de jatos com orifício retangular. Um alto-falante foi utilizado como diafragma e excitado através de um gerador de sinais senoidais para produzir o jato. A frequência de ressonância era desconhecida e foi necessário analisá-la antes de iniciar o experimento. O sistema foi montado em um suporte móvel para que fosse possível variar a posição vertical do gerador de jatos. Foram analisadas as dimensões do orifício para diferentes diâmetros hidráulicos (4 – 8 mm) e razões de aspecto (2 – 4), como também a profundidade da cavidade (2 – 8 mm). Também se analisou a transferência de calor através do impacto de jatos sobre uma placa aquecida. Dentre os estudos, verificaram-se outros parâmetros como o número de Reynolds e o número de Strouhal a fim de calcular a frequência mais adequada para a produção de vórtices. Os resultados demonstraram que para orifícios retangulares, as configurações com diâmetro hidráulico maior e razão de aspecto menor, são as melhores opções para resfriamento dos dispositivos eletrônicos. / With the rapid evolution of technology, electronics have become more compact and with higher processing power, increasing heat generation. Thus, there is a need to develop new forms of cooling, due to the low efficiency of cooling fans and heatsinks used currently. Using synthetic jets for cooling electronic device is still incipient but studies show that this method is an effective alternative. Thus, this work was developed an experimental study with synthetic jets where different configurations were tested with rectangular orifice. A loudspeaker was used as diaphragm and it was excited by a sinusoidal signal generator to produce the jet. The previously unknown ressonant frequency was determined experimentaly as part of this study. The system was mounted on a vertical traverse to allow changes in the vertical position of the synthetic jet generator. Orifice dimensions were analyzed covering variations in hydraulic diameter (4-8 mm) and aspect ratio (2-4), as well as the depth of the cavity (2-8 mm). Also the heat transfer was examined through the jet impingement on a hot plate. Other parameters such as Reynolds and Strouhal number were also examined in order to calculate the best frequency for jet performance. Results show that for rectangular orifice, geometries with larger hydraulic diameter and aspect ratio smaller are the best options for electronic cooling devices.

Solid propellant gas generators that have high gas capacity are used for fast pressurization of inflatable devices or elastic shells. However, many applications such as control surface actuation, air bottle pressurization in rocket engines and safety systems of automobiles (airbags) require exit gases at near ambient temperature. A scheme suitable for short duration applications is passive cooling of gas generator gases by using a packed bed as compact heat exchanger. A study indicated that the mass flow rates of solid propellant gas generators for applications such as air bottle pressurization and control system actuators were of the order of 1 kg/s. Since pressure and enthalpy drop correlations for packed beds with mass flow rates (~1 kg/s) and packing sphere based Reynolds number (Red) ~ 9X104 were unavailable in open literature, an experimental investigation was deemed necessary. The objectives of the present study were (a) characterization of packed beds for pressure and enthalpy drop, (b) develop Euler and Nusselt number correlations at Red~105 and (c) evolve an engineering procedure for estimation of packed bed pressure and enthalpy drop. An experimental test facility with a hydrogen-air combustor was designed and fabricated for this purpose to characterize a variety of packed beds for pressure drop and heat transfer. Flow through separate packed beds consisting of 9.5mm and 5mm steel spheres and lengths ~200mm and ~300mm were studied in the sphere based Reynolds numbers (Red) range of 0.4X104 to 8.5X104. The average porosity (є) of the randomly packed beds was ~0.4. The ratios of packed bed diameter to packing diameter for 9.5mm and 5mm sphere packing were ~ 9.5 and 18 respectively. The inlet flow temperature was unsteady and a suitable arrangement using mesh of spheres was used at either ends to eliminate flow entrance and exit effects. Stagnation pressures were measured at entry and exit of the packed beds. The pressure drop factor fpd, (ratio of Euler number (Eu) to packed bed dimensions) for packed bed with 9.5mm spheres exhibited an asymptotically decreasing trend with increasing Reynolds number, and a correlation for the pressure drop factor is proposed as, fpd=Eu/ [6(1-є) (L/dp)] =125.3 Red-0.4; 0.8X104 < Red < 8.5X104 (9.5mm sphere packing). However, for packed beds with 5mm spheres the pressure drop factor fpd, was observed to increase in the investigated Reynolds number range. The correlation based for pressure drop factor is proposed as, fpd= Eu/ [6(1-є) (L/dp)] =0.0479 Red0.37; 0.4X104 < Red < 3.9X104 (5mm sphere packing). The pressure drop factor was observed to be independent of the inlet flow temperature. Gas temperatures were measured at the entry, exit and at three axial locations along centerline in the packed beds. The solid packing temperature was measured at three axial locations in the packed bed. At Red~104, the influence of gas phase and solid phase thermal conductivity on heat transfer coefficient was found to be negligible based on order of magnitude analysis and solid packing temperature data obtained from the experiments. Evaluation of sphere based Nusselt number (Nud) at axial locations in the packed bed indicated a length effect on the heat transfer coefficient, which was a function of Reynolds number and size of spheres used in packing. The arithmetic average of Nusselt numbers at different axial locations in the packed bed were correlated as Nud=3.85 Red0.5; 0.5X104 < Red < 8.5X104. The Nusselt numbers obtained in the experiments were consistent with corresponding literature data available at lower Reynolds numbers. In this experimental study Euler number correlations for pressure drop and Nusselt number correlations for heat transfer were obtained for packed beds at Red~105. An engineering model for estimation of packed bed pressure and enthalpy drop was evolved, which is useful for sizing of packed bed heat exchanger in solid propellant gas generation systems.

An aluminum NACA 0018 airfoil testbed was constructed with 95 static pressure taps and 25 embedded microphones to enable novel time-resolved measurements of surface pressure. The main objective of this investigation is to utilize time-resolved surface pressure measurements to estimate salient flow characteristics in the separated flow region over the upper surface of an airfoil. The flow development over the airfoil was examined using hot wire anemometry and mean surface pressure for a range of Reynolds numbers from 80x103 to 200x103 and angles of attack from 0° to 18°. For these parameters, laminar boundary layer separation takes place on the upper surface and two flow regimes occur: (i) separation is followed by flow reattachment, so that a separation bubble forms and (ii) separation occurs without subsequent reattachment. Measurements of velocity and mean surface pressure were used to characterize the separated flow region and its effect on airfoil performance using the lift coefficient. In addition, the transition process and the evolution of disturbances were examined. The lift curve characteristics were found to be linked to the rate of change of the separation, transition, and reattachment locations with the angle of attack. For both flow regimes, transition was observed in the separated shear layer. Specifically, the amplification of disturbances within a band of frequencies in the separated shear layer resulted in laminar to turbulent transition. Validation of time-resolved surface pressure measurements was performed for Rec = 100x103 at α = 8° and α = 12°, corresponding to regimes of flow separation with and without reattachment, respectively. A comparative analysis of simultaneous velocity and time-resolved surface pressure measurements showed that the characteristics and development of velocity fluctuations associated with disturbances in the separated shear layer can be extracted from time-resolved surface pressure measurements. Specifically, within the separated flow region, the amplitude of periodic oscillations in the surface pressure signal associated with disturbances in the separated shear layer grew in the streamwise direction. In addition, the frequency at the spectral peak of the amplified disturbances in the separated shear layer was identified. Based on the results of the validation analysis, time-resolved surface pressure measurement analysis techniques were applied for a Reynolds number range from 60x103 to 130x103 and angles of attack from 6° to 16°. Within the separated flow region, the streamwise growth of surface pressure fluctuations is distinctly different depending on the flow regime. Specifically, within the separation bubble, the RMS surface pressure fluctuations increase in the streamwise direction and reach a peak just upstream of the reattachment location. The observed trend is in agreement with that observed for other separating-reattaching flows on geometries such as the forward and backward facing step and splitter plate with fence. In contrast to the separation bubble formation, when the separated shear layer fails to reattach to the airfoil surface, RMS surface pressure fluctuations increase in the streamwise direction with no maximum and the amplitude is significantly lower than those observed in the separation bubble. Surface pressure signals were further examined to identify the frequency, convective velocity, and spanwise uniformity of disturbances in the separated shear layer. Specifically, for both flow regimes, the fundamental frequency and corresponding Strouhal number exhibit a power-law dependency on the Reynolds number. Based on the available data for which velocity measurements were obtained in the separated flow region, the convective velocity matched the mean velocity at the wall-normal distance corresponding to the maximum turbulence intensity. A distinct increase in the convective velocity of disturbances in the separated shear layer was found when the airfoil was stalled in comparison to that found in the separation bubble. From statistical analysis of surface pressure signals in the spanwise direction, it was found that disturbances are strongly two-dimensional in the laminar portion of the separated shear layer and become three-dimensional through the transition process.