Algae-derived biodiesel is currently under investigation as a suitable alternative to traditional fossil-fuels. Though it possesses many favorable characteristics, algae remains prohibitively expensive to mass produce and distribute. The most economical means of growing algae are large-scale open pond raceways. These, however, suffer from low culture densities; this fact impacts the cost directly through diminished productivity, as well as indirectly by raising costs due to the necessity of dewatering low culture density raceway effluent. Algae, as a photosynthetic organism, achieves higher culture densities when sufficient light is provided. In open ponds this can be accomplished by frequently cycling algae to the raceway surface. The current work examined delta wing vortex generators as a means of instigating this cycling motion. In particular the impact of spacing and angle of attack was analyzed. These vortex generators were found to significantly increase vertical mixing when placed in a series, developing precisely the motion desired. Their impact on power requirements was also examined. Specifically it was shown that increases in spacing and decreases in angle of attack result in lower power consumption. It was demonstrated that the most efficient mixing generation is achieved by larger spacings and smaller angles of attack. The impact that these devices had on raceway turbulence as measured by dissipation rate was also investigated and compared to published values for algae growth. Raceways were found to be significantly more turbulent than standard algae environments, and adding delta wings increased these levels further.

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2005. / Includes bibliographical references (p. 99-100).

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2007. / Includes bibliographical references (p. 69-70).

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2007. / Includes bibliographical references (p. 67-69).

Thesis (M.S.)--West Virginia University, 2005. / Title from document title page. Document formatted into pages; contains xiv, 86 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 73-76).

No description available.

The effect of fin and jet vortex generators on the crossflow separation of a 688 class submarine in a turning maneuver was studied. The vortex generators are located on the top and bottom centerline of the submarine. The intent of the vortex generators is to improve turning performance by changing the hydrodynamic forces incurred from crossflow separation. Performance of the jets and the fins are compared. Oil flow visualization and force and moment measurements were used as the primary diagnostics in determining the effectiveness of various vortex generator configurations. The fins were found to be very effective in delaying cross flow separation, while the jets were less effective. In addition, the oil flows revealed the importance of locating vortex generators near the bow and the critical role the sail plays in the fluid dynamics near the submarine. Overall, the fins were found to be viable as a concept for flow control, while the jets were less attractive. / Master of Science

The unsteady interaction of a vortex core with a NACA 0015 airfoil is studied in two dimensions. A two-component, three-beam Helium-Neon laser-Doppler Velocimetry system is used to take data in a water tunnel. Ensemble-averaged velocity fields are obtained in the region of the leading edge of the airfoil. Finite-difference algorithms were written to obtain vorticity and pressure in the data field. Computer animation of the unsteady vorticity was accomplished first with a Fortran code written for an Apple Macintosh computer and later with a commercial software package for a SUN Microsystems graphics terminal. / Master of Science

Approved for public release, distribution is unlimited / An analysis of in-situ aircraft observations collected in the parent cloud of a waterspout is presented. Previous waterspout studies were confined mainly to photometric and model simulated data, no in-situ observations were made internal to the parent cloud. On 27 June 2002 the Cooperative Institute for Remotely Piloted Aircraft Studies (CIRPAS) UV-18A Twin Otter aircraft collected observations in a cloud that had developed in a cloud line, located approximately 15km south of Key West, and that formed a waterspout. This study attempts to analyze the waterspout formation process using these data and through a series of scale interactions, from the synoptic scale down to the individual cloud scale. Based upon the analyzed data a hypothetical formation process is developed. The background synoptic scale flow is shown to establish the necessary ambient shear as a key factor in the waterspout formation. The orientation of mesoscale convergent boundaries and thermodynamic processes, internal to the cloud, proved to be an essential factor in developing the vertical motion patterns necessary for formation of an organized circulation in the shear region and to provide the tipping and stretching of the resultant vortex necessary to account for the waterspout formation. This is consistent with conclusions derived from previous studies. / Captain, United States Air Force

Nas últimas décadas o uso da energia eólica tem apresentado uma maior participação na matriz energética mundial. Como consequência, o tamanho das turbinas eólicas tem aumentado, procurando aproveitar uma quantidade maior de vento e em alturas onde a velocidade é menos afetada pela turbulência atmosférica. Isto gera custos maiores devido ao investimento em novos materiais e tecnologias de fabricação. O projeto de novos perfis aerodinâmicos e o desenvolvimento de técnicas de controle da camada limite têm providenciado melhoras na eficiência aerodinâmica das turbinas, permitindo o aproveitamento de ventos com velocidade média menor, diminuição do efeito da turbulência e conservação do tamanho atual das pás. Uma das técnicas estudadas para o incremento da eficiência aerodinâmica de perfis é a sucção da camada limite, cujo intuito é ampliar a região laminar do escoamento ou adiar a separação deste. Diversos estudos no campo da aviação têm sido desenvolvidos, mostrando resultados promissórios na diminuição do arrasto e aumento da sustentação, mas ainda sem uso comercial. Neste estudo objetivou-se o uso da sucção da camada limite a fim de controlar a separação em um perfil NREL-S809 de uso típico na construção de pás para turbinas eólicas. Assim, foram projetadas três faixas de material perfurado distribuídas no extradorso de um modelo para análise bidimensional, desde o bordo de ataque até 80% da corda. Ensaios aerodinâmicos foram realizados no túnel de vento do Laboratório de Aeronaves da Escola de Engenharia de São Carlos - USP. O ar da camada limite foi sugado através da superfície e os coeficientes de sustentação, arrasto e momento foram medidos. Os resultados foram comparados com o comportamento do perfil base e geradores de vórtice localizados no 10% da corda. O efeito dos geradores de vórtice também foi combinado com aquele produzido pela sucção. Os resultados mostraram que succionar a camada limite aumenta a sustentação principalmente em ângulos de ataque onde a separação é evidente. O efeito da sucção no bordo de ataque adiou ou suavizou o estol, mas presentou maior sensibilidade à presença dos furos quando a sucção foi desligada. Encontrou-se que a sucção é mais eficiente quando a região de sucção é anterior à separação. Neste sentido sucção na parte média da corda (50 < x &#8260; c < 65%) apresentou os melhores resultados quando foi analisado o coeficiente de eficiência em função do coeficiente de sustentação. Este comportamento se mantém ainda para a combinação de sucção e geradores de vórtice, mas preservando muitas das caraterísticas do uso independente destes. Medições da distribuição do coeficiente de pressão no extradorso, mostraram que a sucção distribuída e aplicada em uma região afeta a totalidade da superfície do perfil. Comparações do perfil de velocidades na esteira do bordo de fuga indicaram que o arrasto de forma aumenta quando são usados os geradores de vórtice e diminui quando a sucção é aplicada. / In the last decades the use of wind power has become presenting a greater participation in the world energy matrix. As result, the size of wind turbines has been increased, looking for a larger quantity of wind and the same way high altitudes where the wind speed is less affected by atmospheric turbulence. This leads to higher costs due to investment in new materials and manufacturing technologies. The design of new airfoils and the development of the boundary layer control techniques have provided improvements in the aerodynamic efficiency of the turbines, allowing the harnessing of winds with lower average speeds and lowering the turbulence effect, while the size of turbine blades is keeping. The boundary layer suction has been studied with aim of increase the aerodynamic efficiency of airfoils, in order to extend the laminar region or delay the flow separation. Several studies in the aviation field have been developed, showing promissory results in the drag reduction and lift increasing, however without commercial use. The aim of this study is the boundary layer suction in order to control the separation in a typical airfoil used in the construction of wind turbine blades - NREL-S809. For this purpose three strips of perforated material were located over the upper surface of a model to two-dimentional analysis. The strips were distributed from the leading edge to 80% of the chord. The air in the boundary layer was sucked through the surface and the aerodynamic coefficients of lift, drag and pitch moment were measured. The results were compared with the baseline profile and vortex generators located at 10% of the chord. The effect of the vortex generators has also been combined with that produced by suction. The results showed that the boundary layer suction in the middle of the chord (50% < x &#8260; c < 65%) offers greater increase in the efficiency ratio regarding to maximum lift coefficient. However, boundary layer suction at the leading edge shows both a smoothing and delayed stall. This behavior remains even for the combination of suction and vortex generators, while preserving many of the aerodynamic features of the vortex generators. The main results of the aerodynamic forces were confirmed through pressure coefficient distribution measurements and comparison of the velocity profile in the wake at the trailing edge. The aerodynamic tests were carried out in the wind tunnel of the Aircraft Laboratory of the Escola de Engenharia de São Carlos - USP.