Thesis (M.S.)--University of California, Berkeley, 1961. / "Engineering and Equipment, UC-38" -t.p. "TID-4500 (16th Ed.)" -t.p. Includes bibliographical references (p. 62-63).

No description available.

An experimental evaluation of normal, sonic, helium injection from a wedgeshaped nozzle and a circular nozzle into a Mach 3 free stream with a total pressure of 6.5 atm and a total temperature of 294 K was conducted. The expansion ratio and the mass rate of flow of both nozzles were matched in order to determine the effect of the geometric difference only. 'Decay rate, penetration, and jet area growth rate were used to compare the mixing performance of the nozzles. Oil flow photography was used to determine the size of the three-dimensional boundary layer separation zone in front of each nozzle, and nanoshadowgraph photography was used to visualize the system of shocks and the flow field of each nozzle. Mean flow quantity profiles at several lateral stations were made at three downstream locations. The profiles were used to calculate helium concentration, Mach number, static temperature, static pressure, density, flow velocity, local speed of sound, mass flux, and total pressure. The two nozzles were then compared on the basis of maximum helium concentration decay, core center and overall penetration, and the growth rate and centroid penetration of a defined jet area. Although the decay rate of the jet from the circular nozzle was slightly higher than the decay rate of the jet from the wedge-shaped nozzle, the mixing performance of the wedge-shaped nozzle exceeded that of the circular nozzle in all other comparison parameters. The jet from the wedge-shaped nozzle penetrated further and its area grew more rapidly than the same parameters for the jet from the circular nozzle. The oil flow photography showed that the wedge-shaped nozzle also had no separation zone in front of it, whereas the circular nozzle had a large separation zone. A separation zone in front of a fuel injector in a scramjet engine can result in damage to the combustor from the extreme heat fluxes to the wall. Also, the total pressure loss in the combustor should be lower for fuel injection through a wedge-shaped nozzle due to the elimination of the normal shock. It was concluded that wedge-shaped fuel injectors should perform better than circular fuel injectors in supersonic combustors. / Master of Science

This work discusses the development of a compact Tunable Diode Laser Absorption Spectrometer (TDLAS) for gas phase mixing ratio and temperature measurements of condensible vapors, in particular H2O and D2O, in supersonic flows. Through extensive pressure trace measurements and mass balances on the incoming species, the expected mixing ratio and temperature profiles of the condensible species along the supersonic nozzle have been characterized. Using a Tunable Diode Infrared laser operating in the 8 microns region, the possibility of nonintrusively measuring the gas phase mixing ratio and the temperature (even simultaneously) in a supersonic nozzle is demonstrated. The acquired spectroscopic data and the pressure trace measurements are compared and the results suggest the possibility to improve the instrument set-up and to improve the quality of the measurements. Also, the interpretation of our initial experimental results and the comparison with the pressure traces measurements suggest reasons to further investigate the condensation behavior of D2O and H2O.

The effect of superheat on the disruption of liquid droplets in a compressible gas flow was investigated experimentally in a small-scale, supersonic wind tunnel. Aerodynamically generated ethanol droplets of an average diameter of 0.1 mm were injected via a normal sonic jet into a Mach 1.8 freestream. Both nonsuperheated and superheated droplets were injected with initial Weber numbers of approximately 700. The droplets and flow structure were photographed using the shadowgraph method. The relatively high momentum of the liquid droplets typically caused them to pass out of the sonic jet structure. Nonsuperheated droplets showed no signs of disrupting after traveling over 200 mm downstream from the injection point. Only droplets with injection temperatures above the predicted boiling point at tunnel freestream static pressure (48°C) showed signs of disruption, typically after they left the sonic jet structure (30 to 100 mm downstream of the injection point). Droplets in this range of temperatures appeared to begin to boil from the downstream side of the droplet, shedding a vapor cloud before disrupting completely in the chaotic mode. Droplets with temperatures above the boiling point at the exit plane of the sonic jet began to disrupt in the chaotic mode almost instantly (within 1 exit nozzle diameter).

This thesis describes the commissioning and development of a pulsed supersonic nozzle, Fourier-transform microwave spectrometer and its application to the study of several weakly bound van der Waals complexes. A pulsed supersonic expansion, Fourier-transform microwave spectrometer based on the Flygare design with a number of modifications has been constructed with an operating range of 6-18 GHz. A homodyne detection circuit mixing signals to modulus values between dc and 1 MHz is used, requiring two measurements to determine absolute transition frequencies. Transition frequencies are measured from the power spectrum by determining the first derivative zero crossing point in a least squares fitting procedure. Semiautomation of many of the spectrometer operations has been achieved allowing unattended data collection over scans of up to 300 MHz. The microwave spectrum of Ar₂-OCS and Ar₂-OC³⁴S has been observed and analysed using conventional Watson S reduction hamiltonian parameters. Effective structural parameters are derived and used in a harmonic force field analysis, based on the centrifugal distortion constants, to compare the trimer interations with a model based on the sum of dimer interactions. A series of complexes containing the nitrogen molecule undergoing tunnelling motions have been studied. Hyperfine matrix elements for the first order nuclear quadrupole interaction are derived for the coupled identical nuclei case appropriate to the rapid tunnelling motions observed. The microwave spectrum of N₂-OCS is described. Tunnelling and nuclear spin statistical effects for two symmetry states are observed arising from the interchange of nitrogen nuclei. Rotational and quadrupole constants are derived; an accidental near degeneracy of two rotational levels allows the off-diagonal quadrupole coupling constant to be determined from second order effects. A tunnelling hamiltonian fitting the quadrupole coupling constants to an angular potential has been used to calculate the tunnelling frequency and barrier to N₂ rotation. The microwave spectrum of N₂-O₃ and a preliminary spectrum of N₂-SO₃ have been observed. Rotation-inversion motions of the O₃ and SO₂ moieties must be considered in addition to the N₂ tunnelling to fit the spectrum. Tunnelling frequencies for the O₃/SO₂ and geared motions with the N₂ are derived as well as structural parameters. Modifications for production of refractory molecules and complexes by laser ablation have been made. A modified nozzle employing rods of material is used with the ablation process taking place in the nozzle throat. Modifications to obtain an expansion along the axis of the microwave cavity employ a hemispherical Fabry-Perot cavity configuration. The system has been tested on a number of diatomic molecules including PbS and CuCl.

Ces travaux, initiés par le CNES (Centre National d’Etudes Spatiales) dans le cadre du programme de recherche ATAC (Aérodynamique Tuyères et Arrières-Corps), sont principalement consacrés au développement et à la validation de modèles numériques et physiques, pour la prédiction des charges latérales dans les moteurs-fusées. En effet, les systèmes propulsifs mettent en jeu des phénomènes physiques très complexes : mélange turbulent, compressibilité forte (interaction choc/turbulence, couplage de modes vorticité/entropie/acoustique), structures cohérentes et organisations tourbillonnaires dans le cas tridimensionnel, décollements massifs et instabilités à grande échelle. L’analyse de ces phénomènes nécessite le recourt à des modélisations de plus en plus fines basées sur des simulations numériques avancées. Pour faire face au coût prohibitif des simulations directes (ou simulations LES résolues) des couches limites, un nouveau modèle de paroi a été développé, en se basant sur les propriétés d’auto similarité des couches limites compressibles en tuyères supersoniques, et en utilisant des lois de renormalisation dérivées à partir d’une base de données tabulée. Ce modèle permet de prendre en compte la dynamique de l’écoulement tout en réduisant considérablement le nombre de points de calcul et le pas de temps requis pour les simulations LES. Les résultats de calcul mettent en évidence de nombreuses interactions complexes au sein de l’écoulement. En particulier, les interactions amont/aval (supersonique/subsonique),influençant fortement le décollement et la structure de chocs, à l’origine de l’apparition de pics énergétiques associés à des perturbations acoustiques conduisent à l’apparition,par rétroaction, de phénomènes d’instabilités convectives, couplées à des modes globaux dissymétriques en dynamique absolue. Ces phénomènes auto-entretenus sont synonymes d’efforts latéraux et sont représentatifs des expériences menées en laboratoire et sur bancs d’essai moteurs-fusées. En terme d’optimisation des calculs massivement parallèles, une méthode originale, appelée « Drop-Procs », a été développée dans le cadre des frontières immergées. Cette méthode, adaptée aux architectures de calculs intensifs Tier-0, permet une réduction notable du temps CPU (Central Processing Unit), allant jusqu’à 50%, et rendant ainsi ce type de simulations plus accessible à l’échelle industrielle. / This work, initiated by the CNES (Centre National d’Etudes Spatiales) in the ATAC research program (Aérodynamique Tuyères et Arrières-Corps), is devoted to the development and the validation of numerical and physical models for the prediction of side-loads in rocket engines. Indeed, propulsion systems involve complex physical phenomena : turbulent mixing, high compressibility (interaction shock / turbulence, coupling modes vorticity / entropy / acoustic), coherent structure, three-dimensional vortex organizations, massive detachment and large scale instabilities. The analysis of these phenomena requires the uses of advanced numerical simulations. To deal with the high cost of large-eddy simulations boundary layers, a new wall model, based on renormalization laws and a database, was developed. This model allows to take into account the dynamics of the flow while significantly reducing the number of calculation points and the time step required for LES simulations. Results show many complex interactions with in the flow. In particular, the upstream / downstream interactions (supersonic / subsonic), strongly influence the separation and the shock structure, causing the occurrence of energy peaks associated with acoustic disturbances and leading to the appearance of convective instability, coupled with global asymmetric modes. These self-sustained phenomena are synonymous of side-loads and are representative of laboratory experiments and rocket engine test benches. In terms of optimization of massively parallel computing, a new method, called "Drop-Procs", was developed as part of the immersed boundaries. This method is suitable for compute-intensive architectures Tier-0 and allows a significant reduction in CPU time (Central Processing Unit) consumption, up to 50%, making this type of simulation accessible for industrials.

No description available.

This thesis describes the development and implementation of new computational techniques to predict installation losses for mixed compression inlets and a study of advanced technology nozzles. The new computational techniques have been created to predict drag and total pressure recovery for both axisymmetric and 2-D mixed compression inlet configurations. These inlets are designed for use in aircraft with sustained supersonic cruise capabilities such as the HSCT. The drag and pressure recovery prediction methods have been added to ACSYNT, an aircraft conceptual design program. Also included in this thesis is a survey of the performance of advanced technology nozzles. Axisymmetric and nonaxisymmetric geometries are considered, as are non thrust-vectoring nozzles. Only the internal losses of these nozzles are considered, and these losses are characterized by the thrust coefficient. The results of this survey have also been added to ACSYNT to extend the thrust prediction capabilities of the code. / Master of Science

No description available.