Nonlinear description of transversal motion in a laminar boundary layer with streaks

The nonlinear streamwise growth of a spanwise periodic array of steady streaks in a flat plate boundary layer is numerically computed using the well known Reduced Navier-Stokes formulation. It is found that the flow configuration changes substantially when the amplitude of the streaks grows and the nonlinear effects come into play. The transversal motion (in the wall normal-spanwise plane), which is normally not considered, becomes non-negligible in the nonlinear regime, and it strongly distorts the streamwise velocity profiles, which end up being quite different from those predicted by the linear theory. We analyze in detail the resulting flow patterns for the nonlinearly saturated streaks, and compare them with available experimental results.

Nonlinear description of transversal motion in a laminar boundary layer with streaks

The nonlinear streamwise growth of a spanwise periodic array of steady streaks in a flat plate boundary layer is numerically computed using the well known Reduced Navier- Stokes formulation. It is found that the flow configuration changes substantially when the amplitude of the streaks grows and the nonlinear effects come into play. The transversal motion (in the wall normal-spanwise plane), which is normally not considered, becomes non-negligible in the nonlinear regime, and it strongly distorts the streamwise velocity profiles, which end up being quite different from those predicted by the linear theory. We analyze in detail the resulting flow patterns for the nonlinearly saturated streaks, and compare them with available experimental results.

Optimization of the silicon subcell for III-V on silicon multijunction solar cells: key differences with conventional silicon technology

Dual-junction solar cells formed by a GaAsP or GaInP top cell and a silicon (Si) bottom cell seem to be attractive candidates to materialize the long sought-for integration of III-V materials on Si for photovoltaic (PV) applications. Such integration would offer a cost breakthrough for PV technology, unifying the low cost of Si and the efficiency potential of III-V multijunction solar cells. The optimization of the Si solar cells properties in flat-plate PV technology is well-known; nevertheless, it has been proven that the behavior of Si substrates is different when processed in an MOVPE reactor In this study, we analyze several factors influencing the bottom subcell performance, namely, 1) the emitter formation as a result of phosphorus diffusion; 2) the passivation quality provided by the GaP nucleation layer; and 3) the process impact on the bottom subcell PV properties.

Laminar-turbulent transition induced by a discrete roughness element in a supersonic boundary layer

The linear instability and breakdown to turbulence induced by an isolated roughness element in a boundary layer at Mach 2:5, over an isothermal flat plate with laminar adiabatic wall temperature, have been analysed by means of direct numerical simulations, aided by spatial BiGlobal and three-dimensional parabolized (PSE-3D) stability analyses. It is important to understand transition in this flow regime since the process can be slower than in incompressible flow and is crucial to prediction of local heat loads on next-generation flight vehicles. The results show that the roughness element, with a height of the order of the boundary layer displacement thickness, generates a highly unstable wake, which is composed of a low-velocity streak surrounded by a three-dimensional high-shear layer and is able to sustain the rapid growth of a number of instability modes. The most unstable of these modes are associated with varicose or sinuous deformations of the low-velocity streak; they are a consequence of the instability developing in the three-dimensional shear layer as a whole (the varicose mode) or in the lateral shear layers (the sinuous mode). The most unstable wake mode is of the varicose type and grows on average 17% faster tan the most unstable sinuous mode and 30 times faster than the most unstable boundary layer mode occurring in the absence of a roughness element. Due to the high growthrates registered in the presence of the roughness element, an amplification factor of N D 9 is reached within 50 roughness heights from the roughness trailing edge. The independently performed Navier–Stokes, spatial BiGlobal and PSE-3D stability results are in excellent agreement with each other, validating the use of simplified theories for roughness-induced transition involving wake instabilities. Following the linear stages of the laminar–turbulent transition process, the roll-up of the three-dimensional shear layer leads to the formation of a wedge of turbulence, which spreads laterally at a rate similar to that observed in the case of compressible turbulent spots for the same Mach number.

On the role of global flow instability analysis in closed loop flow control

Control of linear flow instabilities has been demonstrated to be an effective theoretical flow control methodology, capable of modifying transitional flows on canonical geometries such as the plane channel and the flat-plate boundary layer. Extending the well-developed theoretical flow control techniques to flows over or through complex geometries requires addressing the issue of efficient capturing of the leading members of the global eigenspectrum pertinent to such flows. The present contribution describes state-of-the-art modal global instability analysis methodologies recently developed in our group, based on matrix formation and time-stepping, respectively. The relative performance of these algorithms is assessed on the recovery of BiGlobal and TriGlobal eigenspectra in the spanwise periodic and the cubic lid-driven cavity, respectively; the adjoint eigenspectrum in the latter flow is recovered for the first time. For three-dimensional flows without any homogeneous spatial direction, the time-stepping methodology was found to outperform the matrix-forming approach and permit recovering the leading TriGlobal eigenmodes in an three-dimensional open cavity of aspect ratio L : D : W = 5 : 1 : 1; theoretical flow control of this configuration is underway.

A code for direct numerical simulation of turbulent boundary layers at high Reynolds numbers in BG/P supercomputers

A new high-resolution code for the direct numerical simulation of a zero pressure gradient turbulent boundary layers over a flat plate has been developed. Its purpose is to simulate a wide range of Reynolds numbers from Reθ = 300 to 6800 while showing a linear weak scaling up to 32,768 cores in the BG/P architecture. Special attention has been paid to the generation of proper inflow boundary conditions. The results are in good agreement with existing numerical and experimental data sets.

On the role of global flow instability analysis in closed loop flow control

Control of linear flow instabilities has been demonstrated to be an effective theoretical flow control methodology, capable of modifying transitional flow on canonical geometries such as the plane channel and the flat-plate boundary layer.

Entrainment Effects in Turbulent Boundary Layers

Esta tesis estudia el comportamiento de la región exterior de una capa límite turbulenta sin gradientes de presiones. Se ponen a prueba dos teorías relativamente bien establecidas. La teoría de semejanza para la pared supone que en el caso de haber una pared rugosa, el fluido sólo percibe el cambio en la fricción superficial que causa, y otros efectos secundarios quedarán confinados a una zona pegada a la pared. El consenso actual es que dicha teoría es aproximadamente cierta. En el extremo exterior de la capa límite existe una región producida por la interacción entre las estructuras turbulentas y el flujo irrotacional de la corriente libre llamada interfaz turbulenta/no turbulenta. La mayoría de los resultados al respecto sugieren la presencia de fuerzas de cortadura ligeramente más intensa, lo que la hace distinta al resto del flujo turbulento. Las propiedades de esa región probablemente cambien si la velocidad de crecimiento de la capa límite aumenta, algo que puede conseguirse aumentando la fricción en la pared. La rugosidad y la ingestión de masa están entonces relacionadas, y el comportamiento local de la interfaz turbulenta/no turbulenta puede explicar el motivo por el que las capas límite sobre paredes rugosas no se comportan como en el caso de tener paredes lisas precisamente en la zona exterior. Para estudiar las capas límite a números de Reynolds lo suficientemente elevados, se ha desarrollado un nuevo código de alta resolución para la simulación numérica directa de capas límite turbulentas sin gradiente de presión. Dicho código es capaz de simular capas límite en un intervalo de números de Reynolds entre ReT = 100 — 2000 manteniendo una buena escalabilidad hasta los dos millones de hilos en superordenadores de tipo Blue Gene/Q. Se ha guardado especial atención a la generación de condiciones de contorno a la entrada correctas. Los resultados obtenidos están en concordancia con los resultados previos, tanto en el caso de simulaciones como de experimentos. La interfaz turbulenta/no turbulenta de una capa límite se ha analizado usando un valor umbral del módulo de la vorticidad. Dicho umbral se considera un parámetro para analizar cada superficie obtenida de un contorno del módulo de la vorticidad. Se han encontrado dos regímenes distintos en función del umbral escogido con propiedades opuestas, separados por una transición topológica gradual. Las características geométricas de la zona escalan con o99 cuando u^/isdgg es la unidad de vorticidad. Las propiedades del íluido relativas a la posición del contorno de vorticidad han sido analizados para una serie de umbrales utilizando el campo de distancias esféricas, que puede obtenerse con independencia de la complejidad de la superficie de referencia. Las propiedades del fluido a una distancia dada del inerfaz también dependen del umbral de vorticidad, pero tienen características parecidas con independencia del número de Reynolds. La interacción entre la turbulencia y el flujo no turbulento se restringe a una zona muy fina con un espesor del orden de la escala de Kolmogorov local. Hacia el interior del flujo turbulento las propiedades son indistinguibles del resto de la capa límite. Se ha simulado una capa límite sin gradiente de presiones con una fuerza volumétrica cerca de la pared. La el forzado ha sido diseñado para aumentar la fricción en la pared sin introducir ningún efecto geométrico obvio. La simulación consta de dos dominios, un primer dominio más pequeño y a baja resolución que se encarga de generar condiciones de contorno correctas, y un segundo dominio mayor y a alta resolución donde se aplica el forzado. El estudio de los perfiles y los coeficientes de autocorrelación sugieren que los dos casos, el liso y el forzado, no colapsan más allá de la capa logarítmica por la complejidad geométrica de la zona intermitente, y por el hecho que la distancia a la pared no es una longitud característica. Los efectos causados por la geometría de la zona intermitente pueden evitarse utilizando el interfaz como referencia, y la distancia esférica para el análisis de sus propiedades. Las propiedades condicionadas del flujo escalan con 5QQ y u/uT, las dos únicas escalas contenidas en el modelo de semejanza de pared de Townsend, consistente con estos resultados. ABSTRACT This thesis studies the characteristics of the outer region of zero-pressure-gradient turbulent boundary layers at moderate Reynolds numbers. Two relatively established theories are put to test. The wall similarity theory states that with the presence of roughness, turbulent motion is mostly affected by the additional drag caused by the roughness, and that other secondary effects are restricted to a region very close to the wall. The consensus is that this theory is valid, but only as a first approximation. At the edge of the boundary layer there is a thin layer caused by the interaction between the turbulent eddies and the irroational fluid of the free stream, called turbulent/non-turbulent interface. The bulk of results about this layer suggest the presence of some localized shear, with properties that make it distinguishable from the rest of the turbulent flow. The properties of the interface are likely to change if the rate of spread of the turbulent boundary layer is amplified, an effect that is usually achieved by increasing the drag. Roughness and entrainment are therefore linked, and the local features of the turbulent/non-turbulent interface may explain the reason why rough-wall boundary layers deviate from the wall similarity theory precisely far from the wall. To study boundary layers at a higher Reynolds number, a new high-resolution code for the direct numerical simulation of a zero pressure gradient turbulent boundary layers over a flat plate has been developed. This code is able to simulate a wide range of Reynolds numbers from ReT =100 to 2000 while showing a linear weak scaling up to around two million threads in the BG/Q architecture. Special attention has been paid to the generation of proper inflow boundary conditions. The results are in good agreement with existing numerical and experimental data sets. The turbulent/non-turbulent interface of a boundary layer is analyzed by thresholding the vorticity magnitude field. The value of the threshold is considered a parameter in the analysis of the surfaces obtained from isocontours of the vorticity magnitude. Two different regimes for the surface can be distinguished depending on the threshold, with a gradual topological transition across which its geometrical properties change significantly. The width of the transition scales well with oQg when u^/udgg is used as a unit of vorticity. The properties of the flow relative to the position of the vorticity magnitude isocontour are analyzed within the same range of thresholds, using the ball distance field, which can be obtained regardless of the size of the domain and complexity of the interface. The properties of the flow at a given distance to the interface also depend on the threshold, but they are similar regardless of the Reynolds number. The interaction between the turbulent and the non-turbulent flow occurs in a thin layer with a thickness that scales with the Kolmogorov length. Deeper into the turbulent side, the properties are undistinguishable from the rest of the turbulent flow. A zero-pressure-gradient turbulent boundary layer with a volumetric near-wall forcing has been simulated. The forcing has been designed to increase the wall friction without introducing any obvious geometrical effect. The actual simulation is split in two domains, a smaller one in charge of the generation of correct inflow boundary conditions, and a second and larger one where the forcing is applied. The study of the one-point and twopoint statistics suggest that the forced and the smooth cases do not collapse beyond the logarithmic layer may be caused by the geometrical complexity of the intermittent region, and by the fact that the scaling with the wall-normal coordinate is no longer present. The geometrical effects can be avoided using the turbulent/non-turbulent interface as a reference frame, and the minimum distance respect to it. The conditional analysis of the vorticity field with the alternative reference frame recovers the scaling with 5QQ and v¡uT already present in the logarithmic layer, the only two length-scales allowed if Townsend’s wall similarity hypothesis is valid.

A bankable method of assessing the performance of a CPV plant

Concentrating Photovoltaics (CPV) is an alternative to flat-plate module photovoltaic (PV) technology. The bankability of CPV projects is an important issue to pave the way toward a swift and sustained growth in this technology. The bankability of a PV plant is generally addressed through the modeling of its energy yield under a baseline loss scenario, followed by an on-site measurement campaign aimed at verifying its energy performance. This paper proposes a procedure for assessing the performance of a CPV project, articulated around four main successive steps: Solar Resource Assessment, Yield Assessment, Certificate of Provisional Acceptance, and Certificate of Final Acceptance. This methodology allows the long-term energy production of a CPV project to be estimated with an associated uncertainty of ≈5%. To our knowledge, no such method has been proposed to the CPV industry yet, and this critical situation has hindered or made impossible the completion of several important CPV projects undertaken in the world. The main motive for this proposed method is to bring a practical solution to this urgent problem. This procedure can be operated under a wide range of climatic conditions, and makes it possible to assess the bankability of a CPV plant whose design uses any of the technologies currently available on the market. The method is also compliant with both international standards and local regulations. In consequence, its applicability is both general and international.

Control of hypersonic turbulent skin friction by boundary-layer combustion of hydrogen

Shvab-Zeldovich coupling of flow variables has been used to extend Van Driest's theory of turbulent boundary-layer skin friction to include injection and combustion of hydrogen in the boundary layer. The resulting theory is used to make predictions of skin friction and heat transfer that are found to be consistent with experimental and numerical results. Using the theory to extrapolate to larger downstream distances at the same experimental conditions, it is found that the reduction in skin-friction drag with hydrogen mixing and combustion is three times that with mixing alone. In application to flow on a flat plate at mainstream velocities of 2, 4, and 6 knits, and Reynolds numbers from 3 X 10(6) to 1 x 10(8), injection and combustion of hydrogen yielded values of skin-friction drag that were less than one-half of the no-injection skin-friction drag, together with a net reduction in heat transfer when the combustion heat release in air was less than the stagnation enthalpy. The mass efficiency of hydrogen injection, as measured by effective specific impulse values, was approximately 2000 s.

Aquatic passive sampling of herbicides on naked particle loaded membranes: Accelerated measurement and empirical estimation of kinetic parameters

Water-sampler equilibrium partitioning coefficients and aqueous boundary layer mass transfer coefficients for atrazine, diuron, hexazionone and fluometuron onto C18 and SDB-RPS Empore disk-based aquatic passive samplers have been determined experimentally under a laminar flow regime (Re = 5400). The method involved accelerating the time to equilibrium of the samplers by exposing them to three water concentrations, decreasing stepwise to 50% and then 25% of the original concentration. Assuming first-order Fickian kinetics across a rate-limiting aqueous boundary layer, both parameters are determined computationally by unconstrained nonlinear optimization. In addition, a method of estimation of mass transfer coefficients-therefore sampling rates-using the dimensionless Sherwood correlation developed for laminar flow over a flat plate is applied. For each of the herbicides, this correlation is validated to within 40% of the experimental data. The study demonstrates that for trace concentrations (sub 0.1 mu g/L) and these flow conditions, a naked Empore disk performs well as an integrative sampler over short deployments (up to 7 days) for the range of polar herbicides investigated. The SDB-RPS disk allows a longer integrative period than the C18 disk due to its higher sorbent mass and/or its more polar sorbent chemistry. This work also suggests that for certain passive sampler designs, empirical estimation of sampling rates may be possible using correlations that have been available in the chemical engineering literature for some time.

Scramjet lift, thrust and pitching-moment characteristics measured in a shock tunnel

Lift, pitching moment, and thrust/drag on a supersonic combustion ramjet were measured in the T4 free-piston shock tunnel using a three-component stress-wave force balance. The scramjet model was 0.567 m long and weighed approximately 6 kg. Combustion occurred at a nozzle-supply enthalpy of 3.3 MJ/kg and nozzle-supply pressure of 32 MPa at Mach 6.6 for equivalence ratios up to 1.4. The force coefficients varied approximately linearly with equivalence ratio. The location of the center of pressure changed by 10% of the chord of the model over the range of equivalence ratios tested. Lift and pitching-moment coefficients remained constant when the nozzle-supply enthalpy was increased to 4.9 MJ/kg at an equivalence ratio of 0.8, but the thrust coefficient decreased rapidly. When the nozzle-supply pressure was reduced at a nozzle-supply enthalpy of 3.3 MJ/kg and an equivalence ratio of 0.8, the combustion-generated increment of lift and thrust was maintained at 26 MPa, but disappeared at 16 MPa. Measured lift and thrust forces agreed well with calculations made using a simplified force prediction model, but the measured pitching moment substantially exceeded predictions. Choking occurred at nozzle-supply enthalpies of less than 3.0 MJ/kg with an equivalence ratio of 0.8. The tests failed to yield a positive thrust because of the skin-friction drag that accounted for up to 50% of the fuel-off drag.

Continuous property measurement techniques and physics based mathematical model for frost growth control

The development of a new set of frost property measurement techniques to be used in the control of frost growth and defrosting processes in refrigeration systems was investigated. Holographic interferometry and infrared thermometry were used to measure the temperature of the frost-air interface, while a beam element load sensor was used to obtain the weight of a deposited frost layer. The proposed measurement techniques were tested for the cases of natural and forced convection, and the characteristic charts were obtained for a set of operational conditions. ^ An improvement of existing frost growth mathematical models was also investigated. The early stage of frost nucleation was commonly not considered in these models and instead an initial value of layer thickness and porosity was regularly assumed. A nucleation model to obtain the droplet diameter and surface porosity at the end of the early frosting period was developed. The drop-wise early condensation in a cold flat plate under natural convection to a hot (room temperature) and humid air was modeled. A nucleation rate was found, and the relation of heat to mass transfer (Lewis number) was obtained. It was found that the Lewis number was much smaller than unity, which is the standard value usually assumed for most frosting numerical models. The nucleation model was validated against available experimental data for the early nucleation and full growth stages of the frosting process. ^ The combination of frost top temperature and weight variation signals can now be used to control the defrosting timing and the developed early nucleation model can now be used to simulate the entire process of frost growth in any surface material. ^

Análise tribo-termodinâmica da aplicação de nanopartículas de Al2O3 como aditivo lubrificante em compressor hermético de refrigeração

The thermodynamic performance of a refrigeration system can be improved by reducing the compression work by a particular technique for a specific heat removal rate. This study examines the effect of small concentrations of Al2O3 (50 nm) nanoparticles dispersion in the mineral oil based lubricant on the: viscosity, thermal conductivity, and lubrication characteristics as well as the overall performance (based on the Second Law of Thermodynamics) of the refrigerating system using R134a or R600a as refrigerants. The study looked at the influences of variables: i) refrigerant charge (100, 110, 120 and 130 g), ii) rotational speed of the condenser blower (800 and 1100 RPM) and iii) nanoparticle concentration (0.1 and 0.5 g/l) on the system performance based on the Taguchi method in a matrix of L8 trials with the criterion "small irreversibility is better”. They were carried pulldown and cycling tests according to NBR 12866 and NBR 12869, respectively, to evaluate the operational parameters: on-time ratio, cycles per hour, suction and discharge pressures, oil sump temperature, evaporation and condensation temperatures, energy consumption at the set-point, total energy consumption and compressor power. In order to evaluate the nanolubricant characteristics, accelerated tests were performed in a HFRR bench. In each 60 minutes test with nanolubricants at a certain concentration (0, 0.1 and 0.5 g/l), with three replications, the sphere (diameter 6.00 ± 0.05 mm, Ra 0.05 ± 0.005 um, AISI 52100 steel, E = 210 GPa, HRC 62 ± 4) sliding on a flat plate (cast iron FC200, Ra <0.5 ± 0.005 um) in a reciprocating motion with amplitude of 1 mm, frequency 20 Hz and a normal load of 1,96 N. The friction coefficient signals were recorded by sensors coupled to the HFRR system. There was a trend commented bit in the literature: a nanolubricant viscosity reduction at the low nanoparticles concentrations. It was found the dominant trend in the literature: increased thermal conductivity with increasing nanoparticles mass fraction in the base fluid. Another fact observed is the significant thermal conductivity growth of nanolubricant with increasing temperature. The condenser fan rotational speed is the most influential parameter (46.192%) in the refrigerator performance, followed by R600a charge (38.606%). The Al2O3 nanoparticles concentration in the lubricant plays a minor influence on system performance, with 12.44%. The results of power consumption indicates that the nanoparticles addition in the lubricant (0.1 g/L), together with R600a, the refrigerator consumption is reduced of 22% with respect to R134a and POE lubricant. Only the Al2O3 nanoparticles addition in the lubricant results in a consumption reduction of about 5%.