The main aim of this work was to develop a method of screening HgCdTe materials for carrier concentration and mobility using Faraday rotation θ and absorption α. Faraday rotation provides N/m*2, where N is the carrier concentration and m* is the effective mass. Since m* was not known in HgCdTe, a Faraday rotation spectrometer was developed to systematically measure it as a function of temperature and Cd mole fraction. Effective masses in n-InSb, and n-GaAs were measured and compared with known values in the literature to validate the method. Mobility is proportional to θ/α. The proportionalities were determined in HgCdTe, n-InSb, and n-GaAs at infrared wavelengths.

No description available.

Gas turbine blade/vane cooling is obtained by circulating the high pressure air from compressor to the internal cooling passage of the blade/vane. Heat transfer and cooling effect in the rotating blade is highly affected by rotation. The typical rotation number for the aircraft engine is in the range of 0~0.25 and for the land based power generation turbine in the range of 0~05. Currently, the heat transfer data at high rotation numbers are limited. Besides, the investigation of heat transfer phenomena in the turn region, especially near hub portion is rare. This dissertation is to study the heat transfer in rectangular channels with turns in the tip or the hub portion respectively at high rotation numbers close to the engine condition. The dissertation experimentally investigates the heat transfer phenomena in a two-pass rectangular channel (AR=W/H=2:1) with a 180 degree sharp turn in the tip portion. The flow in the first passage is radial outward and after the turn in the second passage, the flow direction is radial inward. The hydraulic diameter (Dh) of the channel is 16.9 mm. Parallel square ribs with an attack angle (alpha) of 45 degrees are used on leading and trailing surfaces to enhance the heat transfer. The rib height-to-hydraulic diameter ratio (e/Dh) is 0.094. For the baseline smooth case and the case with rib pitch-to-height ratio (P/e) 10, channel orientation angles (beta) of 90 degrees and 135 degrees were tried to model the cooling passage in the mid and rear portion of the blade respectively. Two other P/e ratios of 5 and 7.5 were studied at beta=135 degrees to investigate their effect on heat transfer. The data are presented under high rotation numbers and buoyancy parameters by varying the Reynolds number (Re=10,000~40,000) and rotation speed (rpm=0~400). Corresponding rotation number and buoyancy parameter are ranged as 0~0.45 and 0~0.8 respectively. The dissertation also studies the heat transfer in a two-pass channel (AR=2:1) connected by a 180 degree U bend in the hub portion. The flow in the first passage is radial inward and after the U bend, the flow in the second passage is radial outward. The cross-section dimension of this channel is the same as the previous one. To increase heat transfer, staggered square ribs (e/Dh=0.094) are pasted on leading and trailing walls with an attack angle (alpha) of 45 degrees and pitch-to-height ratio (P/e) of 8. A turning vane in the shape of half circle (R=18.5 mm, t=1.6 mm) is used in the turn region to guide the flow for both smooth and ribbed cases. Channel orientation angles (beta) of 90 degrees and 135 degrees were taken for both smooth and ribbed cases. The heat transfer data were taken at high rotation numbers close to previous test section.

We present the results of a new and high sensitivity study of the neutral hydrogen (HI) gas in three early type edge-on spiral galaxies, NGC 4157, NGC 3600 and NGC 2683. All three galaxies reveal HI disks that extend nearly or more than twice the length of the optical disk, which ubiquitously reveal asymmetries and warps. We model each galaxy using a three-dimensional kinematic model to derive the empirical parameters of the density distribution functions and rotation curves. A Gaussian function is unanimously found to best represent the density distribution in the plane of the galaxies. We also find that there is in fact a thick HI disk extending into the halo of two of three of these galaxies with scale heights on kpc. scales. This gas suggests the existence of two separate widespread components: a thin, high intensity disk component, normally rotating, and a vast, low intensity halo component, rotating at slower velocities with respect to the disk. This vertical velocity gradient is perhaps our most significant finding in addition to the discovery of the two new HI halos. We also find an unevenly distributed small-scale component of the gas in the form of shell-like and filamentary structures that extend from the disk into the halo. In all three systems we find unique kinematic and structural peculiarities including an HI disk extending four times the optical disk, a declining rotation curve, a companion, expanding bubbles, disk warps, etc. Several physical parameters are derived such as neutral hydrogen and dynamic masses, systemic velocities, HI radii, HI halo masses, etc. All of our findings are investigated and discussed in depth for each of the three galaxies. / Thesis (Master, Physics, Engineering Physics and Astronomy) -- Queen's University, 2009-09-03 19:47:31.786

Given two sets of points $A$ and $B$ ($|A| = m$, $|B| = n$), we seek to find a minimum-weight many-to-many matching which seeks to match each point in $A$ to at least one point in $B$ and vice versa. Each matched pair (an edge) has a weight. The goal is to find the matching that minimizes the total weight. We study two kinds of problems depending on the edge weight used. The first edge weight is the Euclidean distance, $d_1$. The second is edge weight is the square of the Euclidean distance, $d_2$. There already exists an $O(k\log k)$ algorithm for $d_1$, where $k=m+n$. We provide an $O(mn)$ algorithm for the $d_2$ problem. We also solve the problem of finding the minimum-weight matching when the sets $A$ and $B$ are allowed to be translated on the real line. We present an $O(mnk \log k)$ algorithm for the $d_1$ problem and an $O(3^{mn})$ algorithm for the $d_2$. Furthermore, we also deal with the special case where $A$ and $B$ lie on a circle of a specific circumference. We present an $O(k^2 \log k)$ algorithm and $O(kmn)$ algorithm for solving the minimum-weight matching for the $d_1$, and $d_2$ weights respectively. Much like the problem on the real line, we extend this problem to allow the sets $A$ and $B$ to be rotated on the circle. We try to find the minimum-weight many-to-many matching when rotations are allowed. For $d_1$ we present an $O(k^2mn \log k)$ algorithm and a $O(3^{mn})$ algorithm for $d_2$. / Thesis (Master, Computing) -- Queen's University, 2010-11-08 20:48:18.968

No description available.

No description available.

The purpose of this thesis is the determination of a minimum market price for Short-Rotation Forestry (SRF) willow biomass grown in monoculture and windbreaks in Quebec and Ontario. Full cost budgeting was used and developed on a Microsoft Excel spreadsheet. Harvest cycles of 3 and 4 years for monoculture plantations, and 8 years for windbreaks were investigated. Estimates for establishment and other preharvest costs were obtained from mid-sized (5 hectares) commercial SRF willow plots in Quebec and Ontario. / For the monoculture plantations, irrespective of cycle length, and using the base case figures, the final delivery cost of willow biomass ranged between 74-126 $/odMg and 63--109 $/odMg based on current and projected costs respectively. These hold for yields between 7 and 11 odMg/ha/yr. Moreover, the 4-year cycle was revealed to be more economically efficient than a 3-year cycle. Along with yield, the main cost factors affecting the economics of SRF monoculture plantations are: harvesting, transportation to a processing plant, land lease management. For the two major energy markets, ethanol and electricity production (biomass in replacement of coal), SRF willow biomass in monoculture plantations does not appear to be a viable feedstock given present technology and yields. In the short run, a more promising outlet for willow biomass is space heat production for small buildings, farm complexes, etc. In this market, many potential buyers can afford to pay a higher price for biomass than ethanol or electricity utilities. / In the windbreak system, biomass could be produced for between 44 and 68 $/odMg, assuming that yields between 12 to 20 odMg/ha/yr can be achieved. At this price, windbreak biomass is not a competitive feedstock for ethanol or electricity generation, but is attractive for space heat production. (Abstract shortened by UMI.)

This thesis focused on the conversion period from conventional to organic agriculture for a Quebec dairy farm. The crucial problem resided in developing an economic framework to evaluate alternative crop rotations that would provide farmers in transition an optimal rotation plan compatible with organic farming practices. / Two multi-period linear programming models were developed for that purpose, both models having different assumptions concerning effects that the transition might have on crop yield. / In both transitional models, two crop rotations were selected in the optimal solution. In addition, the establishment of crop rotations was comparable for both models, and this showed that the assumed drop in yield did not have a large impact on the selection of crop rotation. Also, the results support the notion that conversion to organic agriculture had a relatively less negative effect on farm profit if the transition was done gradually.

Open rotors are known to have significant advantages in terms of propulsive efficiency. These advantages translate directly in reduced fuel burn so that they nowadays benefit from a surge of interest. At the same time, recent advances in numerical simulations make the application of multidisciplinary optimization for the demanding design of transonic propeller blades, an affordable option. Therefore, an optimization method in which the performance objectives of aerodynamics, aeroacoustics and aeroelasticity compete against each other, is developed and applied for the design of high-speed single-rotation propellers. The optimization is based on Multi-Objective Differential Evolution (MODE).This technique is a particular kind of evolutionary algorithm that mimics the natural evolution of populations by relying on the selection, recombination and eventually mutation of blade designs, each of them being represented by a vector of design variables (e.g. chord width, tip sweep, etc). MODE has the advantage of dealing concurrently with all the objectives in the selection of potentially promising designs among a population. In order to keep the computational cost within reasonable margins, the assessment of the performance of proposed designs is done in a two-level approach. A metamodel provides performance estimates for each proposed design at extremely low computational effort while high-fidelity analysis codes provide accurate performance values on some promising designs at much higher cost. To safeguard the accuracy of the estimates, the metamodel is initially trained on a population that is specifically assembled for that purpose. The training is repeated from time to time with the high-fidelity performance values of promising designs. Different high-fidelity tools have been developed and used for the assessment of performance.The CFD-tool performs steady RANS simulations of a single blade passage of the isolated propeller in free air under zero angle of attack. These simulations provide the aerodynamic performance values. The full propeller is modelled thanks to cyclic boundary conditions. The k - ε turbulence model is used in combination with wall treatment. Adiabatic no-slip wall conditions are imposed on the spinner and blade surfaces whereas the test-section radial boundary is reproducing the effects of a pressure far-field. This approach has proven its robustness and, above all, its accuracy as satisfactory agreement with experimental results has been found for different operating conditions over a wide range of blade shapes, as well as sufficient grid independency. In the post-processing of the aerodynamic results, the Sound Pressure Level (SPL)is computed for tonal noise at various observer locations by the aeroacoustic solver(CHA). Formulation 1A from Farassat is used for this purpose. This formulation is related to the inhomogeneous wave equation derived from Lighthill's acoustic analogy by Ffowcs Williams and Hawkings (FW-H). It benefits from the partial decoupling of the acoustic and aerodynamic aspects and is particularly suited to compute the noise from propellers. The thickness noise and loading noise are expressed by separate equations in the time-domain whereas the quadrupole source term is dropped from the original FW-H equation. The blade surface is chosen as integration surface and a newly developed truncation technique is applied to circumvent the mathematical singularity arising when parts of the blade reach sonic conditions in terms of kinematics with respect to the observer. This approach delivers accurate values at acceptable computational cost. Besides, CSM-computations make use of a finite elements solver to compute the total mass of the blade as well as the stresses resulting from the centrifugal and aerodynamic forces. Considering the numerous possibilities to tailor the blade structure so that it properly takes on the stresses, only a simplified blade model is implemented. [...]