Summaries in English and Afrikaans / In the following theoretical study the phenomenon of boot camps is described within a penological perspective, as it has originated and developed and is applied in the United States of America. The primary aim of this study is to obtain the Magister Artium degree. Secondly, it sheds light on an alternative method of dispensation of offenders, more specific juvenile offenders, in the criminal justice system. The investigation is intended to make a modest contribution to the content of penology. Knowledge and insight obtained can serve as guidelines for future research in respect of and application of boot camps in South Africa. The planning and functioning of boot camps is taken into account and the rationale behind boot camps as an effective institution of punishment is investigated. This was done against the background of the elements of punishment, over-population of prisons, cost-effectiveness, residivism and rehabilitation. The study is of importance for South African circumstances, because of the increasingly over-population of prisons and the negative effect of imprisonment, especially on juveniles. / In die hieropvolgende teoretiese studie word die verskynsel van boot camps soos wat dit in die Verenigde State van Amerika ontstaan en ontwikkel het en toegepas word, binne 'n penologiese perspektief beskryf. Die beskrywing het in die eerste plek ten doel om die graad Magister Artium te verwerf. Ten tweede werp dit Jig op 'n alternatiewe beskikkingsmetode vir oortreders, veral jeugoortreders, in die regsplegingstelsel. Die doel van die ondersoek is om 'n beskeie bydrae tot die vakinhoud van die penologie te lewer. Kennis en insig wat ingesamel is kan as rigtingwyser dien virtoekomstige navorsing met betrekking tot en toepassing van boot camps in Suid-Afrika. Die beplanning en funksionering van boot camps word in oenskou geneem en die rasionaal van boot camps as 'n effektiewe strafinrigting is ondersoek. Dit is gedoen teen die agtergrond van die elemente van straf, gevangenisoorbevolking, koste-effektiwiteit, residivisme en rehabilitasie. Die studie is van belang vir Suid-Afrikaanse omstandighede weens die toenemende oorbevolking in gevangenisse en nadelige uitwerking van gevangenisstraf op veral jeugoortreders. / Penology / M.A. (Penology)

Ce travail de thèse s’appuie sur une étude expérimentale en tube à choc, plus précisément, c’est une approche expérimentale de l'étude de l'interaction fluide-structure. Considérons un solide indéformable auquel on laisse un degré de liberté en rotation autour d'un axe. Cette structure ferme un espace clos. Si le contenu de l'espace clos subit le passage d'une onde de choc, ce solide va être mis mouvement et tourner autour de son axe. Concrètement, l'onde de choc va augmenter les caractéristiques physiques, en particulier sa pression, du fluide en contact avec la face impactée de cette porte. La face opposée de la porte ne subissant pas ou que très peu l'influence de l'onde de choc, une seule de ses faces est soumise à la surpression. Au moment de l'impact, le déséquilibre ainsi créé impose une action mécanique sur la porte qui va la faire accélérer et tourner autour de son axe de rotation. Jusqu'à ce stade tout est relativement simple. La difficulté intervient à l'instant où la porte commence à s'ouvrir, car les frontières du volume dans lequel le fluide évolue sont modifiées. Des fuites apparaissent et le gaz qui était maintenu dans un volume clos peut maintenant s'écouler vers un milieu libre. Une communication entre les gaz agissant de chaque coté de la porte est créée modifiant leurs propriétés et par conséquent la pression agissant sur chaque côté de la porte. Les actions mécaniques qui s'appliquent sur la porte ne sont plus les mêmes, et par conséquent l'accélération que la porte subit aussi. Au fur et à mesure que la porte change de position, le problème fluide continue d'être modifié et change en retour son action sur la porte. Cette interaction perdure soit jusqu'à ce que les limites du problème cessent d'être modifiées, la porte ne peut plus bouger, ou bien lorsque les actions mécaniques agissant sur la porte s'équilibrent, les fluides de chaque côté de la porte étant dans le même état physique. Le travail présenté ici est une étude des paramètres du fluide ou du solide en mouvement qui sont les acteurs de la loi comportementale gérant ce système complexe. Pour ce faire, nous avons réalisé une maquette expérimentale mettant en action la physique que nous venons de décrire et nous l'avons adaptée à un tube à choc. En éprouvant de nombreuses configurations expérimentales, nous avons pu déterminer comment l'écoulement interne d'un tube à choc évolue lorsqu'il est plus ou moins ouvert à son extrémité. Comment une porte fermée réagit-elle à l'impact d'une onde de choc et quelles en sont les conséquences sur l'évolution des fluides mis en jeu? Quelles sont les conséquences d'une position différente de la porte au moment de l'impact avec l'onde de choc? Ou encore, quel rôle joue l'intensité de l'onde de choc incidente ou l'inertie de la porte sur toute cette dynamique? / This thesis is based on an experimental study carried out in shock tube; in particular, this is an experimental approach to the study of fluid-structure interaction. Consider a rigid body which is allowed to rotate only around an axis and which closes a confined space. If a shock wave crosses the content of the confined space, the body will accelerate and rotate around its axis. Specifically, the shock wave will increase the physical characteristics, especially its pressure, of the fluid acting on the impacted face of the door. The opposite side of the door is not influenced by the incident shock wave, only one of its faces is subjected to overpressure. Following the first impact, the resulting imbalance imposes a mechanical action on the door that will increase its speed and make it turn around its rotation axis. The difficulty comes when the door begins to open: the volume boundaries in which the fluid is contained are modified. Leaks occur and the gas kept in this closed volume can now flow to the atmosphere. Communication between the gas acting on each side of the door is created modifying their properties and consequently the pressure acting on each side of the door.The mechanical actions that apply to the door are no more the same with time, and therefore the acceleration of the door is changing. As the door moves, the fluid problem continues to be changed and in turn it changes its action on the door. This interaction process continues until either the limits of the problem ceases to be changed, the door cannot move, or when the mechanical actions acting on the door are in equilibrium, fluids on each side of the door are in the same physical state. The presented work is a study of the parameters of the fluid or the solid motion which are main actors in the behavioral law managing this complex system. In this aim, we designed an experimental device involving the physics that we have described and we have adapted it to a shock tube. Testing many experimental configurations, we could determine how the internal flow of a shock tube evolves when the end of this shock tube is more or less open.How a closed door reacts to the impact of a shock wave and what are the implications for the evolution of the involved fluids? What are the consequences of a different position of the door at the instant of the impact with the incident shock wave? What role plays the intensity of the incident shock wave or the inertia of the door on this dynamic?

The interaction of a shock wave with a boundary layer is a classic viscous/inviscid interaction problem that occurs over a wide range of high speed aerodynamic flows. For example, on transonic wings, in supersonic air intakes, in propelling nozzles at offdesign conditions and on deflected controls at supersonic/transonic speeds, to name a few. The transonic interaction takes place at Mach numbers typically between 1.1 and 1.5. On an aerofoil, its existence can cause problems that range from a mild increase in section drag to flow separation and buffeting. In the absence of separation the drag increase is predominantly due to wave drag, caused by a rise in entropy through the interaction. The control of the turbulent interaction as applied to a transonic aerofoil is addressed in this thesis. However, the work can equally be applied to the control of interaction for numerous other occurrences where a shock meets a turbulent boundary layer. It is assumed that, for both swept normal shock and unswept normal shock interactions, as long as the Mach number normal to the shock is the same, then the interaction, and therefore its control, should be the same. Numerous schemes have been suggested to control such interaction. However, they have generally been marred by the drag reduction obtained being negated by the additional drag due to the power requirements, for example the pumping power in the case of mass transfer and the drag of the devices in the case of vortex generators. A system of piezoelectrically controlled flaps is presented for the control of the interaction. The flaps would aeroelastically deflect due to the pressure difference created by the pressure rise across the shock and by piezoelectrically induced strains. The amount of deflection, and hence the mass flow through the plenum chamber, would control the interaction. It is proposed that the flaps will delay separation of the boundary layer whilst reducing wave drag and overcome the disadvantages of previous control methods. Active control can be utilised to optimise the effects of the boundary layer shock wave interaction as it would allow the ability to control the position of the control region around the original shock position, mass transfer rate and distribution. A number of design options were considered for the integration of the piezoelectric ceramic into the flap structure. These included the use of unimorphs, bimorphs and polymorphs, with the latter capable of being directly employed as the flap. Unimorphs, with an aluminium substrate, produce less deflection than bimorphs and multimorphs. However, they can withstand and overcome the pressure loads associated with SBLI control. For the current experiments, it was found that near optimal control of the swept and unswept shock wave boundary layer interactions was attained with flap deflections between 1mm and 3mm. However, to obtain the deflection required for optimal performance in a full scale situation, a more powerful piezoelectric actuator material is required than currently available. A theoretical model is developed to predict the effect of unimorph flap deflection on the displacement thickness growth angles, the leading shock angle and the triple point height. It is shown that optimal deflection for SBLI control is a trade-off between reducing the total pressure losses, which is implied with increasing the triple point height, and minimising the frictional losses.

Knowledge of flow separation is very essential for proper understanding of both external and internal aerothermodynamics of bodies. Because of unique flow features such as thick boundary layers, merged shock layers, strong entropy layers, flow separation in the flow field of bodies at hypersonic speeds, is both complex as well as interesting. The problem of flow separation is further complicated at very high stagnation enthalpies because of the real gas effects. Notwithstanding the plethora of information available in open literature even for simple geometric configurations the experimentally determined locations of flow separation and re-attachment points do not match well with the results from the computational studies even at hypersonic laminar flow conditions. In this backdrop the main aim of the present study is to generate a reliable experimental database of classical separated flow features around generic configurations at hypersonic laminar flow conditions. In the present study, flow visualization using high speed camera, surface convective heat transfer rate measurements using platinum thin film sensors, and direct skin friction measurements using PZT crystals have been carried out for characterizing the separated flow field around backward facing step, double cone and double wedge models. The numerical simulations by solving the Navier-Stokes equations have also been carried out to complement the experimental studies. The generic models selected in the present study are simple configurations, where most of the classical hypersonic separated flow features of two-dimensional, axi-symmetric and three dimensional flow fields can be observed. All the experiments are carried out in IISc hypersonic shock tunnel (HST2) at Mach 5.75 and 7.6. For present study, helium and air have been used as the driver and test gases respectively. The high speed schlieren flow visualization is carried out on backward facing step (2 and 3 mm step height), double cone (semi-apex angles of 150/350 and 250/680) and double wedge (semi-apex angles of 150/350) models by using high speed camera (Phantom 7.1). From the visualized shockwave structure in the flow field the flow reattachment point after separation has been clearly identified for backward facing step, double cone and double wedge models at hypersonic Mach numbers while the separation point could not be clearly identified because of the low free stream density in shock tunnels. However the flow visualization studies helped clearly identifying the region of flow separation on the model. Based on the results from the flow visualization studies both the physical location and distribution of platinum thin film gauges was finalized for the heat transfer rate measurements. Surface heat transfer rates along the length of two backward facing step (2 and 3 mm step height) models have been measured using platinum thin film gauges deposited on Macor substrate. The Eckert reference temperature method is used along the flat plate for predicting the heat flux distribution. Theoretical analysis of heat flux distribution down stream of the backward facing step model has been carried out using Gai’s dimensional analysis. The study reveals for the first time that at moderate stagnation enthalpy levels (~2 MJ/kg) the hypersonic separated flow around a backward facing step reattaches rather smoothly without any sudden spikes in the measured values of surface heat transfer rates. Based on the measured surface heating rates on the backward facing step, the reattachment distance was estimated to be approximately 10 and 8 step heights downstream of 2 and 3 mm step respectively at nominal Mach number of 7.6. Convective surface heat transfer experiments have also been carried out on axi-symmetric double cone models (semi-apex angles of 15/35 and 25/68), which is analogous to the Edney’s shock interactions of Type VI and Type IV respectively. The flow is unsteady on the double cone model of 25/68 and measured heat flux is not constant. The heat transfer experiments were also carried out on the three-dimensional double wedge model (semi-apex angles of 15/35). The separation and reattachment points have been clearly identified from the experimental heat transfer measurements. It has been observed that the measured heat transfer rates on the double wedge model is less than the double cone model (semi-apex angles of 150/350) for the identical experimental conditions at the same gauge locations. This difference could be due to the three-dimensional entropy relieving effects of double wedge model. PZT-5H piezoelectric based skin friction gauge is developed and used for direct skin friction measurements in hypersonic shock tunnel (HST2). The bare piezoelectric PZT-5H elements (5 mm × 5 mm with thickness of 0.75 mm) polarized in the shear mode have been used as a skin friction gauge by operating the sensor in the parallel shear mode direction. The natural frequency of the skin friction sensor is ~80 kHz, which is suitable for impulse facilities. The direct skin friction measurements are carried out on flat plate, backward facing step (2 mm step height) and double wedge models. The measured value of skin friction coefficient (integrated over an area of 25 sq. mm; sensor surface area) at a distance of 23 mm from the leading edge of the sharp leading edge backward facing step model is found to be ~ 0.0043 while it decreases to ~ 0.003 at a distance of 43 mm from the leading edge at a stagnation enthalpy of ~ 2MJ/kg. The measured skin friction matches with the Eckert reference temperature within ± 10%. The skin friction coefficient is also measured on the double wedge at a distance of 73 mm from the tip of the first wedge along the surface and is found to be 4.56 × 10-3. Viscous flow numerical simulations are carried out on two-dimensional backward facing step, axi-symmetric double cone and three-dimensional double wedge models using ANSYS-CFX 5.7 package. Navier-Stokes Simulations are carried out at Mach 5.75 and 7.6 using second order accurate (both in time and space) high resolution scheme. The flow is assumed to be laminar and steady throughout the model length except on the double cone (semi-apex angles of 250/680) model configuration, which represents the unsteady flow geometry. Analogous Edney Type VI and Type IV shock interactions are observed on double cone, double wedge (semi-apex angles of 150/350) and double cone (semi-apex angles of 250/680) models respectively from the CFD results. Experimentally measured convective heat transfer rates on the above models are compared with the numerical simulation results. The numerical simulation results matches well with the experimental heat transfer data in the attached flow regions. Considerable differences are observed between the measured surface heat transfer rates and numerical simulations both in the separated flow region and on the second cone/wedge surfaces. The separation and reattachment points can be clearly identified from both experimental measurements and numerical simulations. The results from the numerical simulations are also compared with results from the high speed flow visualization experiments. The experimental database of surface convective heating rates, direct skin friction coefficient and shockwave structure in laminar hypersonic flow conditions will be very useful for validating CFD codes

One of the major technological innovations that are necessary for faster and cheaper access-to-space will be the commercial realization of supersonic combustion jet engines (SCRAMJET). The establishment of the flow through the inlet is one the prime requirement for the success of a SCRAMJET engine. The flow through a SCRAMJET inlet is dominated by inviscid /viscous coupling, transition, shock-shock interaction, shock boundary layer interaction, blunt leading edge effects and flow profile effects. Although the literature is exhaustive on various aspects of flow features associated with SCRAMJET engines, very little is known on the fundamental gasdynamic features dictating the flow establishment in the SCRAMJET inlet. On one hand we need the reduction of flight Mach number to manageable supersonic values inside the SCRAMJET combustor, but on the other hand we have to achieve this with minimum total pressure loss. Hence the dynamics of ramp/cowl shock interaction process ahead of the inlet has a direct bearing on the quality and type of flow inside the SCRAMJET engine. There is virtually no data base in the open literature focusing specifically on the cowl/ramp shock interactions at hypersonic Mach numbers. Hence in this backdrop, the main aim of the present investigation is to systematically understand the ramp/cowl shock interaction processes in front of a generic inlet model. Since we are primarily concerned with the shock interaction process ahead of the cowl all the investigations are carried out without any fuel injection. Variable geometry is necessary if we want to operate the inlet for a wide range of Mach numbers in actual flight. The investigation mainly comprises of three variable geometry configurations; namely, variation of contraction ratios at 00 cowl (CR 8.4, 5.0 and 4.3), variation of cowl length for a given chamber height (four lengths of cowls at 10 mm chamber height) and variation of cowl angle (three angles cowl each for two chamber heights). The change in cowl configuration results in different ramp/cowl shock interaction processes affecting the performance of the inlet. Experiments are performed in IISc hypersonic shock tunnel HST 2 (test time ~ 1 ms) at two nominal Mach numbers 8.0 and 5.74 for design and off-design testing conditions. Exhaustive numerical simulations are also performed to compliment the experiments. Further the effect of concentrated energy deposition on forebody /cowl shock interactions has also been investigated. A 2D, planar, single ramp scramjet inlet model has been designed and fabricated along with various cowl geometries and tested in a hypersonic shock tunnel to characterize the forebody/cowl shock interaction process for different inlet configurations. Further a DC plasma power unit and a plasma torch have been designed, developed and fabricated to serve as energy source for conducting flow-alteration experiments in the inlet model. The V-I characteristics of the plasma torch is studied and an estimation of plasma temperature is also performed as a part of characterizing the plasma flame. Initial standardization experiments of blunt body flow field alteration using the plasma torch and hence its drag reduction, are performed to check the torch’s suitability to be used as a flow-altering device in a shock tunnel. The plasma torch is integrated successfully with the inlet model in a shock tunnel to perform experiments with plasma jet as the energy source. The above experiments are first of its kind to be conducted in a shock tunnel. They are performed at various pressure ratios and supply currents. Time resolved schlieren flow visualization using Phantom 7.1 (Ms Vision Research USA) high speed camera, surface static pressure measurements inside a generic inlet using miniature kulite transducer and surface convective heat transfer rate measurements inside a generic inlet using platinum thin film sensors deposited on Macor substrate are some of the shock tunnel flow diagnostics that have been used in this study. Some of the important conclusions from the study are: • Experiments performed at different contraction ratios show different shock patterns. At CR 8.4, the SOL condition is satisfied, but the flow gets choked due to over contraction and flow through inlet is not established. For CR 5.0, formation of a small Mach stem before the chamber is observed with the reflection point on the cowl and the weak reflected shock entering inside the chamber. The Mach stem grows with time. For CR 4.3, the forebody/cowl shock interference created an Edney’s Type II shock interaction pattern. However, at off-design conditions, for CR 5 the shock reflection is regular and at CR 4.3, the Edney’s Type II pattern lasts for a short time. • For all lengths of cowl tested, 131mm and 141mm showed Edney’s Type II shock interference where as 151mm showed Edney’s Type I pattern at design condition. In all cases the flow is choked for high contraction ratio. At off-design condition these shock patterns do not last for the entire test time but rather it becomes a lambda pattern with the normal shock before the inlet. • For inlet configurations with cowl angle other than 00, the flow is found to be established for all cases at designed condition and except for 100 cowl at off-design condition. • For CR 8.4 the peak value of pressure (~1.7x104 Pa) occurs at a location of 151mm, where as for CR 5.0 and 4.3 they occur at 188mm and 206mm having values ~1.6x104 Pa and ~1.4x104 Pa respectively. These locations indicate the likely locations of shock impingements inside the chamber. • For cowl angle of 00 for a 10 mm chamber the maximum pressure value recorded is ~1.7x104 Pa whereas for 100 and 200 cowl it is ~1.1x104 Pa and 1.2 x104 Pa respectively. This is because in the first case the inlet is choked because of over contraction whereas in the other two cases the CR is less and flow is established inside the inlet. • The average heat transfer rates of last four heat transfer gauges (180 mm, 190 mm, 200 mm and 210 mm from the forebody tip) for all lengths of cowls tested are found to be almost same (~ 20 W/cm2). This is because the flow is choked in all these cases. The numerical simulation also shows uniform distribution here, consistent with the experimental findings. • The locations of heat transfer peaks for 100 cowl at design condition can be observed to be occurring at 170 mm and 200 mm from the forebody tip having values ~44 W/cm2 and ~39 W/cm2 respectively. For a 200 cowl they seem to be occurring at 170 mm and 180 mm from the forebody tip having values ~50 W/cm2 and ~30 W/cm2. These locations indicate the likely locations of shock impingements inside the chamber. With the evolution of concept of upstream fuel injection in recent times these may the most appropriate locations for fuel injection. • At higher jet pressure ratios the plasma jet/ramp shock interaction results in a lambda shock pattern with the triple point forming vertically above the cowl level. This means the normal shock stands in front of the inlet making a part of the flow entering the inlet subsonic. The reflected shock from the triple point also separates the ramp boundary layer. • At lower jet pressure ratios the triple point is formed below the cowl level and the flow entering inside the inlet is supersonic. The reflected shock interacts with the cowl shock and a weak separation shock is seen. • Experiments are performed with concentrated DC electric discharge as energy source. Even though the amount of energy dumped here is less than 0.25% of the total energy it creates a perceptible disturbance in the flow. • Experiments are also performed to see the effect of electric discharge as energy source on height of Mach stem for a given inlet configuration. Deposition of energy in the present location does not seem to alter the Mach stem height. However more experiments need to be performed by varying the energy location to see its effect. Non-intrusive energy sources like microwave and lasers can be thought of as options for depositing energy to study its effect on Mach stem height. Since they provide more flexibility on varying the location of energy the optimum location of energy can be found out for highest reduction of Mach stem height.

Understanding the cellular response thermal stress is important for improving thermoablative treatments of cancer. Cells generally respond to thermal stress by expressing heat shock proteins, or undergoing cell death by apoptosis or necrosis. Most of our detailed knowledge regarding these cellular phenomena has been gathered in vitro in two dimensional (2D) environments. Yet, little is known about how prostate cancer cells respond to thermal stress in a more physiologically relevant three dimensional (3D) environment. Several approaches were used to investigate this question, all of which focused on controlled heating of cells in both two dimensional (2D) and 3D culture. Tools and assays were developed to investigate cellular response to thermal stress in 2D and 3D environments. A computer-controlled heating apparatus was constructed to heat cell cultures to precise temperatures and durations. Three dimensional growth environments were produced using Matrigel, a commercially available extracellular matrix (ecm) mixture. Transcriptional expression of heat shock protein 70 (HSP70) was measured using a green fluorescent protein (GFP) reporter gene under the control of an HSP promoter. Apoptosis, necrosis and HSP70 transcription was measured using flow cytometry analysis. Quantitative polymerase chain reaction (qPCR) and microscopy revealed that transmembrane targets may be involved in the mechanism of the effect which 3D culture has on the cellular response to heat shock. The results herein demonstrate that the 3D growth environment, may be protective to the cell in that the percentage of cells that undergo apoptosis or necrosis when exposed to heat shock are reduced. Furthermore, HSP70 expression is enhanced in 3D culture at a specific thermal dose and integrins and heat shock proteins may be part of the mechanism by which the ecm exerts its protective effect against thermal stress. / text

The interaction of a shock wave with a boundary layer is a classic viscous/inviscid interaction problem that occurs over a wide range of high speed aerodynamic flows. For example, on transonic wings, in supersonic air intakes, in propelling nozzles at offdesign conditions and on deflected controls at supersonic/transonic speeds, to name a few. The transonic interaction takes place at Mach numbers typically between 1.1 and 1.5. On an aerofoil, its existence can cause problems that range from a mild increase in section drag to flow separation and buffeting. In the absence of separation the drag increase is predominantly due to wave drag, caused by a rise in entropy through the interaction. The control of the turbulent interaction as applied to a transonic aerofoil is addressed in this thesis. However, the work can equally be applied to the control of interaction for numerous other occurrences where a shock meets a turbulent boundary layer. It is assumed that, for both swept normal shock and unswept normal shock interactions, as long as the Mach number normal to the shock is the same, then the interaction, and therefore its control, should be the same. Numerous schemes have been suggested to control such interaction. However, they have generally been marred by the drag reduction obtained being negated by the additional drag due to the power requirements, for example the pumping power in the case of mass transfer and the drag of the devices in the case of vortex generators. A system of piezoelectrically controlled flaps is presented for the control of the interaction. The flaps would aeroelastically deflect due to the pressure difference created by the pressure rise across the shock and by piezoelectrically induced strains. The amount of deflection, and hence the mass flow through the plenum chamber, would control the interaction. It is proposed that the flaps will delay separation of the boundary layer whilst reducing wave drag and overcome the disadvantages of previous control methods. Active control can be utilised to optimise the effects of the boundary layer shock wave interaction as it would allow the ability to control the position of the control region around the original shock position, mass transfer rate and distribution. A number of design options were considered for the integration of the piezoelectric ceramic into the flap structure. These included the use of unimorphs, bimorphs and polymorphs, with the latter capable of being directly employed as the flap. Unimorphs, with an aluminium substrate, produce less deflection than bimorphs and multimorphs. However, they can withstand and overcome the pressure loads associated with SBLI control. For the current experiments, it was found that near optimal control of the swept and unswept shock wave boundary layer interactions was attained with flap deflections between 1mm and 3mm. However, to obtain the deflection required for optimal performance in a full scale situation, a more powerful piezoelectric actuator material is required than currently available. A theoretical model is developed to predict the effect of unimorph flap deflection on the displacement thickness growth angles, the leading shock angle and the triple point height. It is shown that optimal deflection for SBLI control is a trade-off between reducing the total pressure losses, which is implied with increasing the triple point height, and minimising the frictional losses.

Summaries in English and Afrikaans / In the following theoretical study the phenomenon of boot camps is described within a penological perspective, as it has originated and developed and is applied in the United States of America. The primary aim of this study is to obtain the Magister Artium degree. Secondly, it sheds light on an alternative method of dispensation of offenders, more specific juvenile offenders, in the criminal justice system. The investigation is intended to make a modest contribution to the content of penology. Knowledge and insight obtained can serve as guidelines for future research in respect of and application of boot camps in South Africa. The planning and functioning of boot camps is taken into account and the rationale behind boot camps as an effective institution of punishment is investigated. This was done against the background of the elements of punishment, over-population of prisons, cost-effectiveness, residivism and rehabilitation. The study is of importance for South African circumstances, because of the increasingly over-population of prisons and the negative effect of imprisonment, especially on juveniles. / In die hieropvolgende teoretiese studie word die verskynsel van boot camps soos wat dit in die Verenigde State van Amerika ontstaan en ontwikkel het en toegepas word, binne 'n penologiese perspektief beskryf. Die beskrywing het in die eerste plek ten doel om die graad Magister Artium te verwerf. Ten tweede werp dit Jig op 'n alternatiewe beskikkingsmetode vir oortreders, veral jeugoortreders, in die regsplegingstelsel. Die doel van die ondersoek is om 'n beskeie bydrae tot die vakinhoud van die penologie te lewer. Kennis en insig wat ingesamel is kan as rigtingwyser dien virtoekomstige navorsing met betrekking tot en toepassing van boot camps in Suid-Afrika. Die beplanning en funksionering van boot camps word in oenskou geneem en die rasionaal van boot camps as 'n effektiewe strafinrigting is ondersoek. Dit is gedoen teen die agtergrond van die elemente van straf, gevangenisoorbevolking, koste-effektiwiteit, residivisme en rehabilitasie. Die studie is van belang vir Suid-Afrikaanse omstandighede weens die toenemende oorbevolking in gevangenisse en nadelige uitwerking van gevangenisstraf op veral jeugoortreders. / Penology / M.A. (Penology)

Plasmodium falciparum is responsible for the most virulent form of human malaria. The biology of the intra-erythrocytic stage of P. falciparum is the most well studied as it is this stage that marks the clinical manifestation of malaria. To establish a successful infection, P. falciparum brings about extensive remodeling of erythrocytes, its host compartment. The infected erythrocytes harbor several parasite induced membranous structures. Most importantly, pathogenesis related structures termed knobs, which impart cytoadherence, appear on the cell surface of the infected erythrocytes. For bringing about such eccentric renovations in its host compartment, the parasite exports 8% of its genome (~400 proteins) to various destinations in the host cell. Studies from our lab have shown that proteins belonging to heat shock protein40 (Hsp40) and heat shock protein70 (Hsp70) group of chaperones are also exported to the host compartment. We and others have implicated these chaperones in important processes such as protein trafficking and chaperoning assembly of parasitic proteins into the cytoadherent knobs. As detailed above, malaria parasite invests a lot of energy in exporting a large number of proteins including chaperones in the red blood cell to meet its pathogenic demands. In order to do so, it heavily relies on its secretory pathway. However, it is known that the parasite experiences a significant amount of oxidative stress on account of heme detoxification, its own metabolism and the immune system of the host. The parasite also effluxes large quantities of reduced thiols such as glutathione and homocysteine into the extracellular milieu indicative of redox perturbation. Additionally, the parasite lacks Peroxiredoxin IV, which otherwise localizes in the ER and carries out detoxification of peroxide generated as a result of oxidative protein folding. Together, these factors indicate that maintaining redox homeostasis is a challenging task for the parasite. It also implies that the ER, where the redox balance is even more critical as it requires oxidising environment for protein folding, is predisposed to stress. In light of this fact and the importance of secretory pathway in malaria pathogenesis, we decided to address the ways and mechanisms used by the parasite to tackle perturbations in its secretory pathway. Examination of a canonical unfolded protein response pathway in P. falciparum ER-stress is a condition arising whenever the load of unfolded proteins increases the folding capacity of the ER. However, eukaryotes have evolved a fairly well conserved homeostatic response pathway known as unfolded protein response (UPR) to tackle ER-stress. This signal transduction pathway is composed of three arms involving three ER-transmembrane signal transducers namely; IRE1, ATF6 and PERK. IRE1 brings about splicing of a bZIP transcription factor, XBP1/Hac1 and ATF6 becomes activated upon getting proteolytically cleaved in the Golgi. These transcription factors then migrate to the nucleus where they bind onto the ER-stress elements thereby, leading to the transcriptional up-regulation of the UPR targets such as ER chaperones and components of ER associated degradation (ERAD) pathway which rescue the function of the ER. PERK on the other hand brings about translational attenuation by phosphorylating eIF2α, thereby providing parasite the benefit of time to recover. We started our examination on UPR in Plasmodium by carrying out in silico analysis of the major components of UPR in the parasite by using Homo sapiens protein sequences as the query. We found that the parasite lacks the homologues of all the transcriptional regulators of canonical UPR. Only PERK component of the UPR was found to be present in the parasite. To rule out the existence of the canonical UPR in P. falciparum, we examined the status of UPR targets by subjecting the parasites to treatment with DTT. DTT perturbs the disulfide oxidation in the ER and thereby inhibits protein folding leading to ER-stress. Owing to the missing components of a canonical UPR, we did not find up-regulation of known UPR targets such as ER-chaperones including PfBiP, PfGrp94, PfPDI and ERAD marker Derlin1 at transcript as well as protein level. Owing to the presence of a PERK homologue, phosphorylation of eIF2α followed by attenuation of protein synthesis was observed upon subjecting the parasites to DTT mediated ER-stress. In the absence of a canonical UPR, the parasites were found to be hypersensitive to ER-stress in comparison to the mammalian counterpart. In the presence of DTT, the parasites showed perturbation in the redox homeostasis as indicated by increase in the levels of ROS. Next, we sought to examine if the parasites resorted to any alternate means of increasing the availability of chaperones in the ER. For this, we analysed the involvement of another Hsp70 family member, Hsp70-x which is homologous to BiP and which is known to traverse the ER while getting exported to the erythrocyte compartment. Interestingly, we found that upon exposure to ER-stress, the export of this protein is partially blocked and around 30% of the protein is retained in the ER. On the other hand, there was no effect on the trafficking of another exported chaperone KAHsp40. This indicates that the parasite possibly recruits this pool of retained Hsp70-x for the chaperoning of unfolded proteins in the ER. Global response to ER-stress in P. falciparum To dig deeper into the parasite specific strategies employed for dealing with ER-stress at a global level, we carried out high throughput transcriptomic and proteomic analysis upon subjecting the parasites to DTT mediated ER-stress. Microarray based gene expression profiling was carried out upon subjecting the parasites to DTT mediated ER-stress. We found that the parasite mounts a transcriptional response as indicated by up-regulation of 155 transcripts. In congruence with our biochemical analysis, we did not find up-regulation of ER chaperones as well as ERAD proteins. Functional grouping of the up-regulated genes revealed large number of hypothetical proteins in our list of differentially expressed genes. The genes encoding exported proteins represent yet another abundant class. In the course of examining the involvement of Plasmodium specific transcriptional regulators mediating response to DTT induced ER-stress, we identified 4 genes belonging to the family of AP2 transcription factors. AP2 (Apetela-2) are specific transcription factors which are possessed by apicomplexa and bring about regulation of developmental processes and stress response in plants. On comparing our list of up-regulated genes with the previously known targets of AP2 factors, we found that an entire cascade of AP2 factors is up-regulated upon DTT-mediated ER stress. Thus, AP2 factors appear to be the major stress response mediators as they are together responsible for the up-regulation of 60% of genes identified in this study. In addition, another striking observation made, was the up-regulation of a few sexual stage specific transcripts. 2D Gel electrophoresis and 2D-DIGE based Proteomic analysis indicated an up-regulation of secretory proteins and some components of vesicular trafficking and secretory machinery possibly to overcome the block in the functions of the secretory pathway. ER-stress triggers stage transition in P. falciparum Intrigued by the up-regulation of a few sexual stage specific genes, we were curious to examine if there was a functional significance of this observation. To this end, we decided to investigate the effect of ER-stress on induction of gametocytes, the only sexual stage found in humans. Indeed, we found a two fold induction in the numbers of gametocytes formed upon challenging the parasite with DTT mediated ER-stress. The induction of gametocytogenesis was also observed by using a clinical isolate of P. falciparum for the assay. The DTT treated cultures progressed through the gametocytogenesis pathway normally forming all the five morphologically distinct stages. Then we sought to examine if this phenomenon could be simulated in the physiological scenario as well. For this, we made use of a rodent model of malaria, P. berghei. Two different treatment regimes involving 1) direct injection of increasing concentration of DTT into P. berghei infected mice and 2) injection of DTT pretreated P. berghei infected erythrocytes into healthy mice were followed. In both cases, a significant increase in the gametocyte induction was observed. Having seen that Plasmodium undergoes gametocytogenesis upon exposure to ER-stress not only in in vitro cultures but also in in vivo scenario, we wanted to identify the players involved in the commitment to sexual stage. Recently, a transcription factor belonging to AP2 class of transcription factors, referred to as AP2-G has been implicated in committing the asexual parasites for transition to gametocyte stage. To examine the role of this factor in the phenotype observed by us, we looked at the effect of DTT on AP2-G. Interestingly, we found around 6 folds up-regulation in the expression of AP2-G levels under ER-stress. The downstream targets of AP2-G, many of which are the markers of gametocyte were also found to be up-regulated upon being exposed to DTT mediated ER-stress indicating the launch of a transcriptional program which together works in the direction of transition to gametocytes. Having seen that P. falciparum undergoes ametocytogenesis in response to DTT treatment both under in vitro and in vivo conditions, we sought to look for probable physiological analogue of DTT. Since glutathione is the major cellular redox buffer, critical for redox homeostasis, we quantitated the levels of both oxidized and reduced forms of this non protein thiol using Mass Spectrometric approach. We found that the levels of reduced forms of glutathione significantly increased upon treating the parasites with DTT. This indicates that the levels of glutathione could be one of the physiological triggers of gametocytogenesis. Conclusion In conclusion, our study analyses the ways and mechanisms employed by malaria parasite to cope with perturbations to its secretory pathway. We have established the absence of a canonical UPR in this parasite and our results suggest that Plasmodium has developed a three stage response to cope with ER stress: 1) an early adaptation to increase the local concentration of chaperones in the ER by partially blocking the export of a Hsp70 family member, 2) activation of gene expression cascade involving AP2 transcription factors and 3) a consequent switch to the transmissible sexual stage. Hence, our study throws light on a novel physiological adaptation utilised by malaria parasite to tackle stress to its secretory pathway. Gametocytogenesis, which can be transmitted to the mosquito vector, could hence serve as an effective means to escape ER-stress altogether. Importantly, while it is widely known that stress brings about switch towards sexual stages in P. falciparum, the molecular triggers involved in this process remain obscure in the field of malaria biology. Therefore, our findings also address this long standing question by providing the evidence of ER-stress being one such trigger required for switching to the transmissible sexual stages.

Shock wave-boundary layer interactions (SWBLIs) have been studied ex-tensively due to their practical importance in the design of high speed ve-hicles. These interactions, especially the ones leading to shock induced separation are typically unsteady in nature and can lead to large fluctuating pressure and thermal loads on the structure. The resulting shock oscil-lations are generally composed of high-frequency small-scale oscillations and low-frequency large-scale oscillations, the source of the later being a subject of intense recent debate. Motivated by these debates, we study in the present work, the SWBLI at a compression ramp and on a forward-facing step (FFS) at a Mach number of 2.5. In the case of compression ramps, a few ramp angles are studied ranging from small (10 degree) ramp angle to relatively large values of up to 28 degrees. The FFS configuration, which consists of a 90 degree step of height h, may be thought of as an extreme case of the compression ramp geometry, with the main geometri-cal parameter here being (h/δ), where δis the thickness of the oncoming boundary layer. This configuration is less studied and has some inherent advantages for experimentally studying SWBLI as the size of the separa-tion bubble is large. In the present experimental study, we use high-speed schlieren, unsteady wall pressure measurements, surface oil flow visualiza-tion, and detailed particle image velocimetry (PIV) measurements in two orthogonal planes to help understand the features of SWBLI in the com-pression ramp geometry and the forward-facing step case. The SWBLI at a compression ramp has been more widely studied, and our measurements show the general features that have been seen in earlier studies. The upstream boundary layer is found to separate close to the ramp corner forming a separation bubble. The streamwise length of the separa-tion bubble is found to increase with the ramp angle, with a consequent shift of the shock foot further upstream. At very small ramp angles up to 10 degrees, there is no evidence of separation, while at large ramp angles of 28 degrees, the separation bubble extends upstream to about 3.5δ(δ=boundary layer thickness). In all cases, the separation bubble is however very small in the wall normal direction, typically known to be about 0.1δ, and hence is difficult to directly measure in experiments using PIV. Shock foot measurements using PIV show that the shock has a spanwise ripple, which seems directly related to the high-and low-speed streaks in the in-coming boundary layer as recently shown by Ganapathisubramani et al. (2007). The forward-facing step configuration may be thought of as an extreme case of the compression ramp geometry, with a ramp angle of 90 degrees. This configuration has not been extensively studied, and is experimentally convenient due to the large separation bubbles formed ahead of the step. In the present work, extensive measurements of the mean and unsteady flow around this configuration have been done, especially for the case of h/δ=2, where his the step height. Pressure measurements in this case, show clear low-frequency motions of the shock at non-dimensional frequencies of about fh/U∞≈ 0.02. In this case, PIV measurements show the pres-ence of a large mean separation bubble extending to about 4hupstream and about 1hvertically. Instantaneous PIV measurements have been done in both cross-stream (streamwise and wall-normal plane) and in the span-wise (streamwise-spanwise) plane. Instantaneous cross-stream PIV mea-surements show significant variations of the shock location and angle, be-sides large variations in the recirculation region (or separation bubble), this being determined as the area having streamwise velocities less than zero. From a large set of individual PIV instantaneous fields, we can estimate the correlation of the measured shock location to both downstream effects like the area of the recirculation region, and upstream effects like the presence of high-/low-speed streaks in the oncoming boundary layer. We find that the shock location measured from data outside the boundary layer is more highly correlated to downstream effects as measured through the recircu-lation area compared to upstream effects in the boundary layer. However, we find that the shock foot within the boundary layer has ripples in the spanwise direction which are well correlated to the presence of high-/low-speed streaks in the incoming boundary layer. These spanwise ripples are however found to be small (less than one h) compared to the highly three-dimensional shape of the recirculation region with spanwise variation of the order of 3 step heights. In summary, the study shows that the separated region ahead of the step is highly three-dimensional. The shock foot within the boundary layer is found to have ripples that are well correlated to fluctuations in the in-coming boundary layer. However, we find that the large-scale nearly two-dimensional shock motions outside the boundary layer are not well cor-related to the fluctuations in the boundary layer, but are instead well cor-related with the spanwise-averaged separation bubble extent. Hence, the present results suggest that for the forward-facing step configuration, it is the downstream effect caused by the separation bubble that leads to the observed low-frequency shock motions.