No description available.

No description available.

No description available.

Coanda-assisted Spray Manipulation (CSM) is a means of modifying the direction of a jet. Previous isothermal static vectoring research is expanded to plasma spray. Two- dimensional Particle Image Velocimetry (PIV) was used to determine the vectoring results for small angles between 5-10°. Suitable parameters were determined for use on a plasma spray gun for small angle vectoring. Three-dimensional PIV was used to determine the elect of high speed rotation on a vectored jet. A 2-piece CSM collar was retrotted to a Praxair SG-100 plasma spray gun that replaced the standard faceplate. Two separate collars were tested: one designed for small vector angles and one for larger vector angles. The small-angle device could modify the trajectory of zirconia powder up to several degrees. Doing so could realign the plasma with the powder, resulting in increased powder temperature and velocity. The large-angle device could vector the plasma jet up to 45°; however the powder did not vector as much. Under large-angle vectoring, the powder velocity and temperature decreased steadily with vector angle. Both devices were tested using a supersonic conguration.

Thesis (M.S.)--West Virginia University, 2004. / Title from document title page. Document formatted into pages; contains x, 77 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 74-77).

This research programme explores, theoretically and experimentally, a new liftsystem for Vertical/Short Take-off and Landing (V/STOL) Aircraft. It is based upon an annular wing wrapped around a centrifugal flow generator, potentially creating a vehicle with no external moving parts, reduced vehicle aerodynamic losses compared to previous V/STOL technologies and substantially eliminating induced drag. It is shown that such a wing works best with a thick aerofoil section, and appears to offer greatest potential at a micro-aerial vehicle scale with regard to fundamental performance parameter “lift to weight ratio”. Certain efficiency losses are encountered mainly occurring from annular flow expansion and problems with achieving acceptable blower slot heights. Experimental methods are described along with results, and a comparison shows that the experimental values remain below theoretical values, partly due to flow asymmetry but possibly also other factors. Symmetrical blowing, as initially hypothesised, was found to be impracticable; this suggested use of pure upper surface blowing with Coanda effect. The modified approach was further explored and proved viable. The ultimate goal of this work was to develop an understanding and the facility to integrate the annular-wing into a vehicle to achieve controlled powered flight. To serve the purpose, issues encountered on current and past V/STOL aircraft are being investigated to set a path for further research/development and to validate/justify the design of future V/STOL aircraft. Also, presented is a feasibility study where different physical scales and propulsion systems are considered, and a turbofan has shown to achieve the best performance in terms of Range and Endurance. This privilege allows one to accurately study the V/STOL technologies around.

O objetivo básico deste trabalho era verificar e quantificar o efeito coanda quando aplicado a um ambiente de atmosfera estagnada na qual a velocidade do escoamento livre é igual a zero. Um aparelho constituído da combinação de um motor e uma hélice combinados com um revestimento externo originalmente utilizado como um componente básico em um túnel de vento experimental. Uma seção de contração de madeira foi projetada e construída para ser unida logo à frente do conjunto hélice/motor, formando um jato retangular. Um aerofólio de seção constante foi testado, formando um jato retangular. Um aerofólio de seção constante foi testado, fixado imediatamente à frente do escoamento do bocal de saída, utilizando uma envergadura igual à largura do jato do bocal de saída. Foram feitas medições do perfil do limite do jato sobre uma distância que excede aquelas incluindo (ambas) as medidas da corda (conhecida do aerofólio). O perfil de velocidade do escoamento induzido sobre a superfície superior de um aerofólio de seção NASA GA(w)-1 foi tomado para um aerofólio limpo e com uma faixa com rugosidade num ponto próximo ao bordo de ataque. O aerofólio foi testado com e sem a faixa de rugosidade, com pontos de tomada de pressão estática ao longo de sua corda fornecendo assim sua distribuição de pressão. O aerofólio foi testado para ângulos de ataque entre zero a quarenta e cinco graus referentes à ilha do escoamento do jato. Os resultados foram registrados e analisados conseqüentemente. / The basic objective of this work was to verify and quantify the Coanda Effect when applied to a stagnent atmosphere in which the free stream velocity was zero. An apparatus consisting of a motor and fan combination combined with external fairings originally used in an experimental wind tunnel was used as the basic component. A wooden contraction section was designed and built to be joined immediately downstream of the fan/motor combination, providing a rectangular jet. A constant section airfoil was tested, suspended immediately downstream of the outlet mouth using a span length equal to that of the mouth of the jet. Measurements were made of the jet limit profile over a distance that exceeded that including the aerofoil chord. The velocity profile induced by the jet flow over the upper surface of a NASA GA(W)-1 section aerofoil was measured for the clean one and with a roughness strip in place near the leading edge. The aerofoil was tested with chordwise static pressure points along the centerline giving the respective pressure distribution, also with and without a roughness strip added. There were different tests for angles of attack with reference to the jet centerline between zero and forty five degrees. The results were registered and analysed accordingly.

O objetivo básico deste trabalho era verificar e quantificar o efeito coanda quando aplicado a um ambiente de atmosfera estagnada na qual a velocidade do escoamento livre é igual a zero. Um aparelho constituído da combinação de um motor e uma hélice combinados com um revestimento externo originalmente utilizado como um componente básico em um túnel de vento experimental. Uma seção de contração de madeira foi projetada e construída para ser unida logo à frente do conjunto hélice/motor, formando um jato retangular. Um aerofólio de seção constante foi testado, formando um jato retangular. Um aerofólio de seção constante foi testado, fixado imediatamente à frente do escoamento do bocal de saída, utilizando uma envergadura igual à largura do jato do bocal de saída. Foram feitas medições do perfil do limite do jato sobre uma distância que excede aquelas incluindo (ambas) as medidas da corda (conhecida do aerofólio). O perfil de velocidade do escoamento induzido sobre a superfície superior de um aerofólio de seção NASA GA(w)-1 foi tomado para um aerofólio limpo e com uma faixa com rugosidade num ponto próximo ao bordo de ataque. O aerofólio foi testado com e sem a faixa de rugosidade, com pontos de tomada de pressão estática ao longo de sua corda fornecendo assim sua distribuição de pressão. O aerofólio foi testado para ângulos de ataque entre zero a quarenta e cinco graus referentes à ilha do escoamento do jato. Os resultados foram registrados e analisados conseqüentemente. / The basic objective of this work was to verify and quantify the Coanda Effect when applied to a stagnent atmosphere in which the free stream velocity was zero. An apparatus consisting of a motor and fan combination combined with external fairings originally used in an experimental wind tunnel was used as the basic component. A wooden contraction section was designed and built to be joined immediately downstream of the fan/motor combination, providing a rectangular jet. A constant section airfoil was tested, suspended immediately downstream of the outlet mouth using a span length equal to that of the mouth of the jet. Measurements were made of the jet limit profile over a distance that exceeded that including the aerofoil chord. The velocity profile induced by the jet flow over the upper surface of a NASA GA(W)-1 section aerofoil was measured for the clean one and with a roughness strip in place near the leading edge. The aerofoil was tested with chordwise static pressure points along the centerline giving the respective pressure distribution, also with and without a roughness strip added. There were different tests for angles of attack with reference to the jet centerline between zero and forty five degrees. The results were registered and analysed accordingly.

The aerodynamic forces and moments on an axisymmetric body of revolution are controlled in a low-speed wind tunnel by induced local flow attachment. Control is effected by an array of aft-facing synthetic jets emanating from narrow, azimuthally segmented slots embedded within an axisymmetric backward facing step. The actuation results in a localized, segmented vectoring of the separated base flow along a rear Coanda surface and induced asymmetric aerodynamic forces and moments. The observed effects are investigated in both quasi-steady and transient states, with emphasis on parametric dependence. It is shown that the magnitude of the effected forces can be substantially increased by slight variations of the Coanda surface geometry. Force and velocity measurements are used to elucidate the mechanisms by which the synthetic jets produce asymmetric aerodynamic forces and moments, demonstrating a novel method to steer axisymmetric bodies during flight.

Thesis (M.S.)--California Polytechnic State University, 2010. / Title from PDF title page; viewed on May 20, 2010. Major professor: David Marshall, Ph.D. "Presented to the faculty of California Polytechnic State University, San Luis Obispo." "In partial fulfillment of the requirements for the degree [of] Master of Science in Aerospace Engineering." "April 2010." Includes bibliographical references (p. 80-82).