Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Meteorology, 1979. / Microfiche copy available in Archives and Science. / Bibliography : leaves 151-154. / by Joseph Stephen Scire. / M.S.

Thesis. 1977. M.S.--Massachusetts Institute of Technology. Dept. of Meteorology. / Microfiche copy available in Archives and Science. / Bibliography : leaves 99-101. / M.S.

We propose the use of a small unmanned aerial vehicle (UAV) equipped with temperature, pressure, and relative humidity sensors to estimate sensible and latent heat fluxes over an active agricultural area in east-central Mississippi. The Bowen ratio method is applied to vertical soundings from the surface to 120 meters at 10-meter intervals. A number of flights were conducted at Mississippi State University during the late stages of the growing season with the purpose of obtaining heat flux estimates over different land surface/cover types. Results show that the UAV platform is able to provide reasonable heat and moisture flux estimates, and that the fluxes show substantial variability among different land cover types over a small spatial scale. Future work must be done to quantify the diurnal and seasonal changes in heat flux estimates over various crop types and investigate flight plans and sensor mounting options to maximize sensor precision.

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<p>Hypersonic flow over two generic missile configurations was investigated using CFD meth-</p> <p>ods. CFD results were compared with experimental results obtained by the hypersonic flight</p> <p>lab at Texas A&M University. Baseline RANS computations involving the missile configurations at a zero deg angle-of-attack were performed, along with computations at higher angles-of-attack. As the angle-of-attack was increased, complex vortex interactions were observed in the region between the fins. Increasing the angle-of-attack generally increased heating on the windward side of the missile geometries, especially on wall surface regions</p> <p>adjacent to the fin-root vortices. The results presented highlight observed fin region vortices and regions of intense heating on the body surface. DES simulations methods were also used to explore unsteady aspects of flow around the two generic missile configurations through time-accurate CFD simulations. Power spectral plots were generated to quantify the dominant frequencies of large-scale unsteadiness.</p>

Black liquor is an intermediate product of pulp production. Recovery boilers process black liquor to recover the inorganic material for recycling in the mill and to generate electricity and steam for the paper mill. Black liquor droplet combustion rates and mechanisms dictate many aspects of recovery boiler performance. This investigation documents new experimental data on single droplet pyrolysis and combustion in a laboratory furnace that mimics many of the essential features of commercial boilers (temperature, composition, droplet size, etc.). These experiments monitored single droplets placed on a thermocouple wire and suspended from a mass balance. Simultaneous video images and pyrometry data provide mass loss and internal temperature data. These investigations provide an extensive data set from which to validate a model and insight into the mechanisms of combustion. Particles burning in air expelled ejecta from the particle during the entire combustion process, though ejection rates during the late stages of char combustion were observed to be higher than during other stages. In addition, char burning began almost the instant the particle entered the reactor; showing significant overlap in the combustion processes. A transient, 1-dimensional, single-droplet model describes droplet combustion. This model solves the momentum, energy, species continuity, and overall continuity equations using the control volume method. The model uses the power-law scheme for combined advection diffusion, and the fully-implicit scheme for the time step. It predicts internal velocities, gas and solid temperatures (assumed equal), pressure, and composition. Pressure and velocity equations use Darcy's Law for flow through a porous medium. Modeling results show the large effect of swelling on all particle properties. This model describes the flame region by extending the control volume into the gas phase.

Since its introduction in the 1980's, the Adomian Decomposition Method (ADM) has proven to be an efficient and reliable method for solving many types of problems. Originally developed to solve nonlinear functional equations, the ADM has since been used for a wide range of equation types (like boundary value problems, integral equations, equations arising in flow of incompressible and compressible fluids etc...). This work is devoted to an evaluation of the effectiveness of this method when used for fluid dynamic applications. In particular, the ADM has been applied to the Blasius equation, the Falkner-Skan equation, and the Orr-Sommerfeld equation. This study is divided into five Chapters and an Appendix. The first chapter is devoted to an introduction of the Adomian Decomposition method (ADM) with simple illustrations. The Second Chapter is devoted to the application of the ADM to generalized Blasius Equation and our result is compared to other published results when the parameter values are appropriately set. Chapter 3 presents the solution generated for the Falkner-Skan equation. Finally, the Orr-Sommerfeld equation is dealt with in the fourth Chapter. Chapter 5 is devoted to the findings and recommendations based on this study. The Appendix contains details of the solutions considered as well as an alternate solution for the generalized Blasius Equation using Bender's delta-perturbation method.

The passage shock wave end wall boundary layer interaction in a transonic compressor was investigated with a laser transit anemometer. A two stage transonic compressor designed without inlet guide vanes was used in this flow field investigation. Measurements of the flow velocity were made within the first stage rotor passage of this transonic compressor. Laser measurements were made in two blade passages at six axial locations from 10% of the axial blade chord in front of the leading edge to 30% of the axial blade chord into the blade passage. At three of these axial locations, laser traverses were taken at different radial immersions to investigate the flow behavior near the tip end wall. Twenty-six different locations were traversed circumferentially. The measurements reveal that the end wall boundary layer in this region is separated from the core flow by what appears to be a shear layer where the passage shock wave and all ordered flow seem to end abruptly. / Ph. D. / incomplete_metadata

Measurements were made in a zero pressure gradient turbulent boundary layer over two roughness patches containing hemispherical and cubical elements. The elements were 3 mm in height and spaced 16.5 mm apart in an array containing 7 streamwise rows and 6 spanwise columns for a total of 42 elements per patch. The boundary layer thickness was approximately 60 mm, so the ratio of element height to that thickness was a large amount at k/δ = 20. A three velocity component laser Doppler velocimeter measured instantaneous velocities. Mean flow and turbulence statistics were calculated as well velocity energy spectra. Surface pressure fluctuations were measured using a two-microphone subtraction method. The results show that hemispherical elements produce larger turbulence quantities in their wakes compared to the cubes. This is due to the hemispheres having a frontal area nearly 60% larger than that of the cubes. The turbulence levels behind the hemispheres is a maximum behind the first streamwise row of elements, and decreases afterwards. The cubical elements maintain a nearly constant amount of turbulence in their wake, signifying little interaction between cubical elements. Surface pressure fluctuations vary little in the streamwise direction of the patches. The hemispherical elements produce a larger sound pressure level behind them than the cube elements do. Velocity spectra results show large normal stress energy for regions at and below the element height. The energy for locations high in the boundary layer increases as the flow moves downstream. Coherency plots show that there is a large correlation between the turbulent structure and production of shear stress at the roughness height. Any measurements taken at or below the roughness height are highly correlated under 10 kHz, while locations higher in the boundary layer are correlated under 2 kHz. / Master of Science