There is a demand for a whole field velocimetry technique which offers the capability of rapid characterisation of complex engineering flow fields. This thesis describes a research programme aimed at the development of a reliable Doppler global velocimeter, suited to the measurement of such flows. The programme of work undertaken is discussed with reference both to research undertaken elsewhere and to previous work on the system at Oxford. While much of the underlying technology required for the construction of an accurate and reliable velocimeter has already been studied in Oxford and elsewhere, little attention has been paid by previous workers to the examination of the impact of data processing techniques on attainable flow measurement accuracy. In the present work, a number of image processing methods have been utilised for Doppler global velocimetry data processing. Those methods are described here, together with a theoretical analysis of their expected performance when applied to Doppler global velocimetry data. The expected error resulting from image processing considerations and also from the physical characteristics of the Doppler global velocimetry hardware are quantified in such a way that error estimates may be computed for real measured data frames. The results of the application of the velocimeter to the simple test case of measuring a velocity component of a rotating disc are presented. The velocimeter was subsequently applied to the measurement of a free jet flow and to a transonic flow field in a convergent-divergent nozzle. Correlations with accepted velocity field values were undertaken, and compared to the expected error previously determined. The choice of image processing algorithms was found to be of great importance in terms of Doppler global velocimetry measurement accuracy.

ABSTRACT CONCEPTUAL INTERNAL DESIGN AND COMPUTATIONAL FLUID DYNAMICS ANALYSIS OF A SUPERSONIC INLET ALEMDAROgLU, Mine M. S., Department of Aerospace Engineering Supervisor: Prof. Dr. Yusuf &Ouml / ZY&Ouml / R&Uuml / K May 2005, 144 pages In this thesis, the conceptual internal design of the air inlet of a supersonic, high altitude, solid propellant ramjet cruise missile is performed. Inviscid, compressible CFD analysis of the designed inlet is made in order to obtain qualitative and quantitative performance characteristics of the inlet at different operating conditions. The conceptual design of the inlet is realized by using analytical relations and equations, correlations derived from numerous available past experimental data and state-of-the-art design examples. The performance estimation of the designed inlet at different operating conditions is done by using one and two dimensional gas dynamics equations. The results of the performance estimation study are compared with the results of the CFD analysis and these results are discussed in detail. A commercial tool, CFD-FASTRAN&Ograve / , is used for the CFD analysis. Inlet flow phenomena such as, different shock patterns and shock positions, performance degradation at off-design operating conditions and inlet unstart are observed. Keywords: Supersonic Inlet, Ramjet, CFD, Inlet Performance Characteristics, Operating Conditions, Unstart

The aerodynamics phenomena of flapping motion in hover are considered in view of the future Micro Air Vehicle applications. The aim of this work is to characterize the vortex dynamics generated by the wing in motion using direct numerical simulation and experimental analysis then to propose a simplified analytical model for prediction of the forces in order to optimize the parameters of the motion leading to maximum force. A great number of cases are investigated corresponding to different angles of attack, location of start of change of incidence, location of start of change of velocity, axis of rotation, and Re number. The airfoil used is symmetrical. The flow is assumed to be incompressible and laminar with the Reynolds numbers between 500 and 2000. The experimental results obtained by the laser sheet visualization and the Particle Image Velocimetry (PIV) techniques are used in parallel with the direct numerical simulation results for the phenomenological analysis of the flow. The model developed for the aerodynamic forces is an indicial method based on the use of the Duhamel Integral and the results obtained by this model are compared with the ones of the numerical simulations.

In this thesis, a new turbulence model developed previously for channel and flat plate flows is evaluated for flat plate flows with pressure gradient. For this purpose a flow solver, which uses boundary layer equations as the governing equations and Von Karman momentum integral equation for the calculation of skin friction, is developed. It is shown that the error of the new turbulence model, in predicting the velocity profile, is less than 5 % for the flat plate flows without pressure gradient and less than 10 % for the flat plate flows with favorable pressure gradient. It is also shown that results with an error in the order of 20 % can be achieved for the flat plate flows with adverse pressure gradient.

A three dimensional wing design tool with analysis functions has been developed with embedded Euler/Navier-Stokes flow solver and a three dimensional hyperbolic grid generator. A graphical user interface has been constructed using PYTHON script language and the tool was enhanced with pre-processing and post-processing capabilities. Analysis and design procedures are demonstrated with automatic grid generation, automatic series solution and automatic graphs and reports generation.

The study presented in this thesis comprises the development of the longitudinal autopilot algorithm for a ramjet powered air-to-surface missile. Ramjet Missiles have short time-of-flight, however they suffer from limited angle of attack margins due to poor operational-region characteristics of the ramjet engine. Because of such limitations and presence of uncertainties involved, Robust Control Techniques are used for the controller design. Robust Control Techniques not only provide an easy limitation/uncertainty/performance handling for MIMO systems, but also, robust controllers promise stability and performance even in the presence of uncertainties of a pre-defined class. All the design process is carried out in such a way that at the end of the study a tool has been developed, that can process raw aerodynamic data obtained by Missile DATCOM program, linearize the equations of motion, construct the system structure and design sub-optimal H&amp / #8734 / controllers to meet the requirements provided by the user. An autopilot which is designed by classical control techniques is used for performance and robustness comparison, and a non-linear simulation is used for validation. It is concluded that the code, which is very easy to modify for the specifications of other missile systems, can be used as a reliable tool in the preliminary design phases where there exists uncertainties/limitations and still can provide satisfactory results while making the design process much faster.

Auf dem Gebiet der Flugnavigation hat die Darstellung raumbezogener Information traditionell eine herausragende Bedeutung ...

The thesis introduces a new quantitative safety modelling approach for large scale socio-technical systems that exhibit Low Probability High Consequence (LPHC) accidents. This approach uses Bayesian Belief Networks (BBN) and overcomes inherent difficulties of current methods, difficulties that make these methods incapable of coping with complexities of socio-technical systems.

Thesis (M.Sc.)--Memorial University of Newfoundland. / Typescript. Bibliography: leaves 142-147. Also available online.

Made available in DSpace on 2014-06-11T19:28:34Z (GMT). No. of bitstreams: 0 Previous issue date: 2006-03-06Bitstream added on 2014-06-13T20:18:25Z : No. of bitstreams: 1 souzafilho_mp_me_guara.pdf: 3830984 bytes, checksum: 7c2960cef5b04e4cbf20952bbc3f0443 (MD5) / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Este trabalho teve como objetivo o desenvolvimento das técnicas fundição de semicubos do trem de pouso principal do cargueiro C-115 Buffalo da Força Área Brasileira, pelo processo de fundição de liga de magnésio em moldes de areia a verde para atender as necessidades emergenciais nas atividades de apoio logístico, tático e transporte. Por ser um item estrutural cujas exigências em relação às propriedades de engenharia e segurança são rigorosas, foi necessário o desenvolvimento de técnicas de fundição diferenciadas para a obtenção do modelo com suas respectivas superespessuras de contração e usinagem; ângulos de saída; sistemas especiais de canais de alimentação; molde preparado com areia sintética, bentonita, enxofre, ácido bórico e água; magnésio, alumínio, zinco e alumínio-manganês de grau metalúrgico para a obtenção da liga; tratamento e refino do banho metálico, técnica de vazamento com frentes de alimentação simétricas; controle de qualidade por meio de inspeção visual, análise da composição química e metalográfica das fases e constituintes da liga, ensaios mecânicos e radiográficos para qualificação do fundido, conforme padrões aeronáuticos. Os ensaios apresentaram resultados cujos valores obtidos foram comparados com os padrões aeronáuticos internacionais, permitindo viabilizar a transferência desse desenvolvimento para o processo produtivo de forma a atender necessidades emergenciais e estimular a evolução do setor aeronáutico do País. / This work had as objective the development of the techniques of semicubes casting of the main landing gear of the C-115 Buffalo freighterm from Brazilian Air Force, by the process of magnesium alloy casting in green sand molds to attend to the emergent necessities in the activities of logistic, tactical support and air service. The creation of the Project of Nationalization of Aeronautical Components was necessary for the maintenance of the operationalization of the aircraft and to prevent the collapse of the fleet. Aeronautical wells are a structural item whose requirements in relation to the security and engineering properties are rigorous, it was necessary the development of differentiated techniques of casting for the attainment of the model with its respective superthicknesses contraction adn machining; pattern draft; special gate systems; mold prepared in synthetic sand, bentonite sand, sulphur, acid boric and water; magnesium, aluminium, zinc and aluminum-manganese of metallurgical degree for obtention of the alloy; treatment and refining of the metallic bath, pouring technique with symmetrical fronts of feeding; quality control by means of visual inspection, analysis of the chemical and metallographic composition of the phase and mechanical and radiografic constuent of the alloy, assays for qualification of the casting, as aeronautical standards. The assays had presented resulted whose gotten values had been compared with international aeronautical standards, allowing to make possible the transference of this devolopment for the productive process to pay attention to emergency necessities and to stimulate the evolution of the aeronautical sector of the Country.