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.

Les travaux présentés dans ce mémoire de thèse s’inscrivent dans le cadre des études liées aux dégâts sur les structures et les blessures subies par les personnes à la suite d’explosions de charges explosives en milieu confiné et semi-confiné. Afin de mener cette étude, des expériences sont réalisées à petite échelle en laboratoire et sont complétées par des simulations numériques. Les ondes de choc sont obtenues grâce à la détonation d’une charge explosive gazeuse composée de propane-oxygène en proportion stoechiométrique. L’étude consiste donc à réaliser des expériences à petite échelle en laboratoire afin d’apprécier les champs de pression obtenus à la suite de la détonation d’une charge explosive au sein de deux configurations différentes. La première représente un atelier pyrotechnique et la seconde met en jeu un entrepôt de stockage de bouteilles de gaz. Les résultats expérimentaux sont ensuite confrontés à des résultats obtenus par simulations numériques réalisées grâce au logiciel AUTODYN. En complément de ces deux configuration principales, une étude est menée sur l’identification des pics de surpressions réfléchis grâce à une approche expérimentale appelée paroi par paroi. Une étude est également menée sur la détermination d’une équivalence massique entre le TNT et le mélange gazeux utilisé pour les expériences. / The goal of this study is to investigate shock waves propagation, in a geometrically complex confined and semi-confined environment, consecutive to the detonation of a spherical explosive charge. In this objective, small scale experiments are conducted in laboratory and are completed with numerical analysis. Shock waves are generated thanks to spherical detonation of a gas mixture composed of propane-oxygen in stoechiometric proportion. Two main configurations are studied: the first represents a pyrotechnic workshop and the second is a warehouse containing gas cylinder. Experimental and numerical results are then compared. Complementary studies are realised to describe blast wave propagation inside a semi-confined volume thanks to a new experimental approach named wall by wall. Finally, in order to simulate TNT charges detonation by computational means, an important study is conducted to determine a mass equivalent between TNT and gas mixture.

Shock-shock interactions are among the most basic gas-dynamic problem, and are almost unavoidable in any high speed light, where shock waves generating from different sources crosses each other paths. These interactions when present very close to the solid surface lead to very high pressure and thermal loads on the surface. The related practical problem is that experienced at the cowl lip of a scramjet engine, where the interfering shock waves leads to high heat transfer rates which may also lead to the damage of the material. The classification by Edney (1968) on the shock-shock interaction patterns based on the visualization has since then served the basis for such studies. Though the problem of high heating on the surface in the vicinity of the shock-shock interactions has been studied at length at supersonic Mach numbers, the study on the topic at the hypersonic Mach numbers is little sparse. Even in the studies at hypersonic Mach numbers, the high speeds are not simulated, which is the measure of the kinetic energy of the ow. Very few experimental studies have addressed this problem by simulating the energy content of the ow. Also, some of the numerical studies on the shock-shock interactions suggest the presence of unsteadiness in the shock-shock interaction patterns as observed by Edney (1968), though this observation is not made very clearly in the experimental studies undertaken so far. In the present study, experiments are carried out in a conventional shock tunnel at Mach number of 5.62 (total enthalpy of 1.07 MJ/kg; freestream velocity of 1361 m/s), with the objective of mapping the surface pressure distribution and surface convective heat transfer rate distribution on the hemispherical body in the presence of the shock-shock interactions. A shock generator which is basically a wedge of angle = 25 , is placed at some dis-dance in front of the hemispherical body such that the planar oblique shock wave from the shock generator hits the bow shock wave in front of the hemi-spherical body. The relative distance between the wedge tip and the nose of the hemispherical body is allowed to change in di erent experiments to capture the whole realm of shock-shock interaction by making the planar oblique shock wave interact with the bow shock wave at different locations along its trajectory. The study results in a bulk of data for the surface pressure and heat transfer rates which were obtained by placing 5 kulites pressure transducers, 1 PCB pressure transducer and 21 platinum thin lm gauges along the surface of the hemispherical body in a plane normal to the freestream velocity direction. Along with the measurement of the surface pressure and the surface heat transfer rates, the schlieren visualization is carried out to capture the shock waves, expansion fans, slip lines, present in a certain shock-shock interaction pattern and the measured values were correlated with the captured schlieren images to evaluate the ow build up and steady and useful test time thereby helping in understanding the ow physics in the presence of the shock-shock interactions. From the present study it has been observed that in the presence of Edney Type-I and Edney Type-II interaction, the heat transfer rates on the hemi-spherical body are symmetrical about the centerline of the body, with the peak heating at the centerline which drops towards the shoulder. For Edney Type-III, Edney Type-IV, Edney Type-V and Edney Type-VI interaction pattern, the distribution in not symmetrical and shifts in peak heat transfer rates being on the side of the hemispherical from which planar oblique shock wave is incident. Also, it is observed that for the interactions which appear within the sonic circle, Edney Type-III and Edney Type-IV, the heat transfer rates observe an unsteadiness, such that the gauges located close to the interaction region experiencing varying heat transfer rates during the useful test time of the shock tunnel. Few experiments were conducted at Mach 8.36 (total enthalpy of 1.29 MJ/kg; freestream velocity of 1555.25 m/s) and Mach 10.14 (total enthalpy of 2.67 MJ/kg; freestream velocity of 2258.51 m/s) for the con gurations representing Edney Type-III interaction pattern to further evaluate the unsteady nature observed at Mach 5.62 ows. The unsteadiness was evident in both the cases. It is realized that the short test times in the shock tunnels pose a constraint in the study of unsteady flow fields, and the use of tailored mode operation of shock tunnel can alleviate this constraint. Also, limited number of experiments in the present study, which are carried out in a Free Piston Shock Tunnel, helps to understand the need to conduct such study in high enthalpy test conditions.

Underwater explosions pose a significant threat to waterborne infrastructure though destructive pressure waves that can travel significant distances through the water. However, the use of bubble screens can attenuate the peak pressure and energy flux created by explosions to safe levels. This study investigates the prediction of pressure wave characteristics based on accumulated data, the damage potential of underwater explosions based on applied loads and effective material strength, and the bubble screen parameters required to prevent damage. The results were compiled to form a procedure for the design and implementation of a bubble screen the protection of waterborne infrastructure.

No description available.

<p>The compressible turbulent boundary layer developing over atwo-dimensional bump which leads to a supersonic pocket with aterminating shock wave has been studied. The measurements havebeen made with hot-wire anemometry and Particle ImageVelocimetry (PIV).</p><p>A method to calibrate hot-wire probes in compressible ow hasbeen developed which take into account not only the ow velocitybut also the inuence of the Mach number, stagnation temperatureand uid density. The calibration unit consists of a small jetow facility, where the temperature can be varied. The hot wiresare calibrated in the potential core of the free jet. The jetemanates in a container where the static pressure can becontrolled, and thereby the gas density. The calibration methodwas verfied in the at plate zero pressure gradient turbulentboundary layer in front of the bump at three different Machnumbers, namely 0.3, 0.5 and 0.7. The profiles were alsomeasured at different static pressures in order to see theinuence of varying density. Good agreement between the profilesmeasured at different pressures, as well as with the standardlogarithmic profile was obtained.</p><p>The PIV measurements of the boundary layer ow in front ofthe 2D bump showed good agreement with the velocity profilesmeasured with hotwire anemometry. The shock wave boundary layerinteraction was investigated for an inlet Mach number of 0.69.A lambda shock wave was seen on the downstream side of thebump. The velocity on both sides of the shock wave as measuredwith the PIV was in good agreement with theory. The shock wavewas found to cause boundary layer separation, which was seen asa rapid growth of the boundary layer thickness downstream theshock. However, no back ow was seen in the PIV-data, probablybecause the seeding did not give enough particles in theseparated region. The PIV data also showed that the shock wavewas oscillating, i.e. it was moving approximately 5 mm back andforth. This distance corresponds to about five boundary layerthicknesses in terms of the boundary layer upstream theshock.</p><p><b>Descriptors:</b>Fluid mechanics, compressible ow,turbulence, boundary layer, hot-wire anemometry, PIV, shockwave boundary layer interaction, shape factor.</p>

Lorsqu'un phénomène de détonation survient dans des milieux confinés comme un bâtiment présentant un système de galeries, l'onde de choc générée se propage et peut engendrer des dégâts matériels et humains considérables. En effet, l’onde de choc en se propageant dans ces systèmes de canaux confinés va interagir avec les obstacles qu’elle rencontre (humains et matériels), et va provoquer de très fortes élévations de la pression localement. Ce phénomène peut être très destructeur pour les structures et létale pour les humains. L'objectif de cette étude, expérimentale et numérique, est donc d'étudier la propagation d'une onde de choc dans différents systèmes de canaux afin de comprendre son comportement et de proposer des solutions pour en atténuer les dégâts. L’étude s’articule autour de deux grands axes. Le premier étudie de manière très académique la propagation d’une onde de choc au travers de cinq configurations différentes ; deux sans variation de section (un coude à 45$^{\circ}$ et un coude à 90$^{\circ}$), et trois avec variation de section (un divergent, un élargissement brusque et une bifurcation en « Y »). L’influence de la singularité sur la pression réfléchie en fond de configuration est étudiée ainsi que les mécanismes physiques complexes qui se produisent derrière l’onde de choc le long de la singularité. Le deuxième axe étudie l’atténuation de la pression réfléchie par l’ajout de piège (cavités) le long du système étudié. Une étude paramétrique montre que la position ainsi que la taille et la forme du piège ont un impact sur l’atténuation de l’onde de choc. / In the search for protection from explosions phenomena, a variety of underground shelters were studied to minimize the risks related to the propagation of shock waves in closed areas. Indeed, the blast effect could be really destructive for equipment and humans encountering the shock wave propagation, because of the high elevation of the local pressure it generates. Thus, the propagation of a shock wave through various canal systems is both experimentally and numerically studied. This study is based on two topics. The first part is focused on the study of the propagation of a shock wave through five various configurations ; two whithout aera change (a 45$^{\circ}$ bend duct and a 90$^{\circ}$ bend), and three configurations whith a sectional enlargement (a divergent, an abrupt area change and a « Y » bifurcation). The impact of the geometry on the end wall reflected pressure is studied as well as some complex physical mechanisms that occur behind the incident shock wave. The second part explores the mitigation of the pressure level in the device with the addition of traps (cavities) along the studied configuration. A parametric study based on the shape and size of the cavities, shows that these parameters have a considerable impact on the pressure level in the duct system.

Introdução: A terapia com ondas de choque tem sido proposta como forma de tratamento para doença de Peyronie, mesmo não se conhecendo exatamente qual o mecanismo de ação das ondas de choque na placa fibrótica desta doença. A principal hipótese postulada para o mecanismo de ação é a neovascularização estimulada pelas ondas de choque, com conseqüente liberação de óxido nítrico e diminuição dos fatores inflamatórios através da ação dos macrófagos. Alguns estudos em humanos mostraram resultados favoráveis na melhora da dor peniana e do desempenho sexual após utilização da terapia com ondas de choque, no entanto até o momento não existe nenhum trabalho demonstrando a existência de lesões no tecido peniano adjacente à placa fibrótica, ou até mesmo se há formação de novas placas. Objetivo: O objetivo deste estudo é determinar a existência de lesões estruturais teciduais no pênis de coelhos, após a utilização da terapia com ondas de choque. Métodos: Para o estudo foram utilizados vinte e cinco coelhos machos adultos da linhagem New Zeeland White, divididos em três grupos: Grupo I: Controle - Composto por cinco animais, que foram submetidos a três sessões de ondas de choque, com dois mil disparos cada, de intensidade de 15 KV; neste grupo, foi colocada uma placa protetora de borracha entre o equipamento de litotripsia e o pênis. Os animais foram sacrificados sete dias após a última sessão. Grupo II: Tratado com avaliação precoce - Composto por dez animais que foram submetidos a três sessões de ondas de choque, com dois mil disparos, de intensidade de 15 KV, diretamente sobre o pênis. Os animais foram sacrificados após sete dias da última sessão. Grupo III: Tratado com avaliação tardia - Composto por dez animais que foram submetidos a três sessões de ondas de choque, com dois mil disparos, de intensidade de 15 KV, diretamente sobre o pênis. Os animais foram sacrificados noventa dias após a última sessão para análise histológica e morfométrica. Resultados: Macroscopicamente foram observados hematomas, petéquias e equimoses em 100% e uretrorragia em 57,9% dos animais dos grupos tratados, sintomas esses que regrediram após 48 horas. Microscopicamente foram observadas lesões como degeneração da camada basal somente no grupo tratado com avaliação precoce em 55,6%, papilomatose e acantose nos dois grupos tratados em 22,2%, congestão da derme em 100% dos animais do grupo tratado com avaliação precoce e 80% dos animais do grupo tratado com avaliação tardia e espessamento da túnica albugínea em 80% dos animais do grupo tratado com avaliação tardia. A histomorfometria da túnica albugínea mostrou média de 16,6% de fibras de colágeno no grupo controle, 20,9% no tratado com avaliação precoce e 49,1% no tratado com avaliação tardia (p<0,001) causando desorganização e remodelamento da túnica. Não houve diferença estatística na porcentagem de fibras musculares nos corpos cavernosos entre os grupos, sendo a média no grupo controle de 54,6%, no grupo tratado com avaliação precoce de 56,1% e no grupo tratado com avaliação tardia de 47,8% (p=0,214). Conclusão: A terapia com ondas de choque é um método que produz lesões teciduais em todos os planos do pênis com aumento da quantidade das fibras de colágeno na túnica albugínea e provocando assim um remodelamento e desorganização da túnica albugínea / Introduction: Extracorporeal shockwaves (ESWL) have been proposed as a treatment for Peyronie\'s disease. Objective: The aim of this study is to determine whether there is any injury to the normal penile tissue during ESWL in rabbits. Methods: 25 adult male NZW rabbits undergone to 3 sessions of ESWL . Divided into 3 groups: Group I(no shock) - 5 animals. Group II(Short-term effect) - 10 animals, sacrificed 7 days. Group III(Long-term effect) - 10 animals evaluated 90 days after the last session. The penile tissue was analyzed. Results: Macroscopically was observed the presence of hematomas, petechias and equimosis. Histological evaluation demonstrated the presence of basal cell degeneration, papilomathosis, acanthosis, congestion and fibrosis of the albuginea with increase of collagen fibers. Conclusion: ESWL produce injury in all tissues of the penis

by Lo, Kin Yin Anthony. / Thesis (M.Phil.)--Chinese University of Hong Kong, 2011. / Includes bibliographical references (leaves 168-195). / Abstracts in English and Chinese. / Abstract --- p.i / Declaration --- p.V / Publications and Conference Presentations --- p.vi / Scholarships and Awards --- p.vii / Acknowledgements --- p.viii / Table of contents --- p.X / Abbreviations --- p.xiv / List of Figures --- p.xvi / List of Tables --- p.xvii / Chapter 1. --- General Introduction --- p.1 / Chapter 2. --- Literature Review --- p.7 / Chapter 2.1 --- Introduction of nephrolithasis and surgical management --- p.9 / Chapter 2.1.1 --- Epidemology and physiochemistry --- p.9 / Chapter 2.1.2 --- Surgical management of nephrolithasis parallel with stone factors --- p.15 / Chapter 2.2 --- Extracorpoeral Shock Wave Lithotripsy in present study --- p.17 / Chapter 2.2.1 --- The 4th generation - Sonolith Vision electroconductive lithotripter --- p.18 / Chapter 2.2.2 --- The role of shock wave delivery rate in treatment outcome and its prediction --- p.23 / Chapter 2.2.3 --- Patient-controlled analgesia during Shock Wave Lithotripsy treatment and its pain management --- p.29 / Chapter 2.2.4 --- Shock wave induced renal injury & the use of urinary biomarker --- p.35 / Chapter 3. --- Materials and Methods --- p.62 / Chapter 3.1 --- Study Design --- p.63 / Chapter 3.2 --- Patient Selection --- p.64 / Chapter 3.3 --- Treatment Protocol --- p.63 / Chapter 3.4 --- Sample size calculation --- p.68 / Chapter 3.5 --- Statistical analysis --- p.68 / Chapter 4. --- The effect of shock wave delivery rate on treatment outcome and its prediction --- p.69 / Chapter 4.1 --- Introduction --- p.70 / Chapter 4.2 --- Materials and Methods --- p.72 / Chapter 4.2.1 --- ESWL treatment protocol --- p.72 / Chapter 4.2.2 --- Outcome Assessment --- p.73 / Chapter 4.2.3 --- Mathematical model development --- p.75 / Chapter 4.2.4 --- Statistical analysis --- p.76 / Chapter 4.3 --- Results --- p.77 / Chapter 4.3.1 --- Baseline characteristics and treatment modalities --- p.78 / Chapter 4.3.2 --- ESWL treatment outcome --- p.79 / Chapter 4.3.3 --- Mathematical model --- p.81 / Chapter 4.4 --- Discussion --- p.82 / Chapter 4.4.1 --- Overall treatment outcome improved by the use of slower rate --- p.82 / Chapter 4.4.2 --- When should we use fast/slow rate? --- p.86 / Chapter 4.4.3 --- Mathematical model to predict ESWL outcome --- p.88 / Chapter 4.5 --- Conclusion --- p.91 / Chapter 5. --- The role of shock wave delivery rate and patient-controlled analgesia in pain --- p.101 / Chapter 5.1 --- Introduction --- p.102 / Chapter 5.2 --- Materials and Methods --- p.104 / Chapter 5.2.1 --- ESWL treatment protocol and PCA settings --- p.104 / Chapter 5.2.2 --- Outcome Assessment --- p.105 / Chapter 5.2.3 --- Statistical analysis --- p.107 / Chapter 5.3 --- Results --- p.108 / Chapter 5.3.1 --- Baseline characteristics and treatment modalities --- p.108 / Chapter 5.3.2 --- Pain experience and satisfaction with PCA at different shock wave delivery rates --- p.108 / Chapter 5.3.3 --- Correlation between rate pain --- p.110 / Chapter 5.3.4 --- Vital signs --- p.110 / Chapter 5.4 --- Discussion --- p.111 / Chapter 5.4.1 --- Adverse complication was mild with PCA using alfentanil --- p.111 / Chapter 5.4.2 --- Less pain experience with 60 SWs/min --- p.112 / Chapter 5.4.3 --- Why PCA usage was the same in both groups? --- p.112 / Chapter 5.4.4 --- No correlation with treatment outcome --- p.114 / Chapter 5.5 --- Conclusion --- p.115 / Chapter 6. --- "The relations among rate of shock wave delivery, induced renal injury and acute complications" --- p.128 / Chapter 6.1 --- Introduction --- p.129 / Chapter 6.2 --- Materials and Methods --- p.130 / Chapter 6.2.1 --- ESWL treatment protocol --- p.130 / Chapter 6.2.2 --- Outcome Assessment --- p.131 / Chapter 6.2.3 --- Statistical analysis --- p.136 / Chapter 6.3 --- Results --- p.137 / Chapter 6.3.1 --- Baseline characteristics and treatment modalities --- p.137 / Chapter 6.3.2 --- Quality control of creatinine and NAG --- p.137 / Chapter 6.3.3 --- Standard curves ofIL-18 and NGAL --- p.137 / Chapter 6.3.4 --- Higher levels of urinary NAG and IL-18 in 60 SWs/min group --- p.138 / Chapter 6.3.5 --- Similar levels of urinary NGAL in both groups --- p.138 / Chapter 6.3.6 --- Unplanned hospital visits were similar in both groups --- p.139 / Chapter 6.4 --- Discussion --- p.140 / Chapter 6.4.1 --- More tubular damages caused by slower rate --- p.140 / Chapter 6.4.2 --- Escalated inflammatory activities in 60 SWs/min --- p.141 / Chapter 6.4.3 --- Vascular damage and ischemic insults were the same in both groups? --- p.142 / Chapter 6.4.4 --- Post-operative complications are similar in both groups --- p.142 / Chapter 6.4.5 --- 60 SWs/min vs. 120 SWs/min - What makes the difference in renal injury? --- p.143 / Chapter 6.5 --- Conclusion --- p.145 / Chapter 7. --- Discussion --- p.154 / Chapter 7.1 --- General discussion --- p.155 / Chapter 8. --- Conclusion --- p.158 / Chapter 8.1 --- General conclusion --- p.159 / Appendix --- p.160 / Appendix I --- p.161 / Appendix II --- p.163 / References --- p.167

The increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in fullscale, due to the uncertainties involved in modeling andpredicting the flow phenomena involved. In the present work the causes of unsteady and unsymmetricalflow separation and resulting side-loads in rocket enginenozzles are investigated. This involves the use of acombination of analytical, numerical and experimental methods,which all are presented in the thesis. A main part of the workis based on sub-scale testing of model nozzles operated withair. Hence, aspects on how to design sub-scale models that areable to capture the relevant physics of full-scale rocketengine nozzles are highlighted. Scaling laws like thosepresented in here are indispensable for extracting side-loadcorrelations from sub-scale tests and applying them tofull-scale nozzles. Three main types of side-load mechanisms have been observedin the test campaigns, due to: (i) intermittent and randompressure fluctuations, (ii) transition in separation patternand (iii) aeroelastic coupling. All these three types aredescribed and exemplified by test results together withanalysis. A comprehensive, up-to-date review of supersonic flowseparation and side-loads in internal nozzle flows is givenwith an in-depth discussion of different approaches forpredicting the phenomena. This includes methods for predictingshock-induced separation, models for predicting side-loadlevels and aeroelastic coupling effects. Examples are presentedto illustrate the status of various methods, and theiradvantages and shortcomings are discussed. A major part of the thesis focus on the fundamentalshock-wave turbulent boundary layer interaction (SWTBLI) and aphysical description of the phenomenon is given. Thisdescription is based on theoretical concepts, computationalresults and experimental observation, where, however, emphasisis placed on the rocket-engineering perspective. This workconnects the industrial development of rocket engine nozzles tothe fundamental research of the SWTBLI phenomenon and shows howthese research results can be utilized in real applications.The thesis is concluded with remarks on active and passive flowcontrol in rocket nozzles and directions of futureresearch. The present work was performed at VAC's Space PropulsionDivision within the framework of European spacecooperation. Keywords:turbulent, boundary layer, shock wave,interaction, overexpanded,rocket nozzle, flow separation,control, side-load, experiments, models, review.