This document describes a study on the uniformity of pressure profiles in a wind tunnel. It begins with background information on the development of wind tunnels. It then describes the experimental setup of the uni-insta's wind tunnel, which features a bell mouth entry, honeycomb settling chamber, and acrylic working section. Pressure measurements were taken at six points in the working section using a probe and manometer. Graphs of the pressure readings show the pressure distribution was nearly uniform, with small variations between the five static pressure ports. The document concludes the wind tunnel achieved good simulation of atmospheric boundary layers and uniform flow.
The document describes an experiment to measure the uniformity of velocity in a wind tunnel. A hot wire anemometer system was used to measure the absolute, axial, vertical, and perpendicular velocity values at 6 points as a probe was moved through the test section of the wind tunnel. The results showed a range of velocities from 26.12 to 39.18 m/s, indicating a lack of uniformity. Graphs of the velocity measurements also revealed deviations. It was concluded that the non-uniform flow was likely due to the wind tunnel's contraction ratio of 9, which is below the recommended ratio of around 16 needed to achieve uniform flow. Improving the design of the contraction and suction sides could help address the issue.
IRJET- Design and Fabrication of an Open Circuit Subsonic Wind Tunnel for Edu...IRJET Journal
This document describes the design and fabrication of a low-cost subsonic wind tunnel for educational purposes. Key aspects include:
1) The wind tunnel was designed and built by students and a professor to support fluid mechanics experiments at their university on a limited budget.
2) Design considerations included achieving a test section air speed over 10m/s, compact size, ease of use, and longevity.
3) Components like the contraction cone, diffuser, test section, and flow conditioner were designed and fabricated based on guidelines from literature.
4) Experimental testing showed average air speeds in the test section of 12.9m/s, with variations within 1m/s. CFD simulation
International Journal of Engineering Research and Development (IJERD)IJERD Editor
journal publishing, how to publish research paper, Call For research paper, international journal, publishing a paper, IJERD, journal of science and technology, how to get a research paper published, publishing a paper, publishing of journal, publishing of research paper, reserach and review articles, IJERD Journal, How to publish your research paper, publish research paper, open access engineering journal, Engineering journal, Mathemetics journal, Physics journal, Chemistry journal, Computer Engineering, Computer Science journal, how to submit your paper, peer reviw journal, indexed journal, reserach and review articles, engineering journal, www.ijerd.com, research journals,
yahoo journals, bing journals, International Journal of Engineering Research and Development, google journals, hard copy of journal
International Journal of Modern Engineering Research (IJMER) is Peer reviewed, online Journal. It serves as an international archival forum of scholarly research related to engineering and science education.
International Journal of Modern Engineering Research (IJMER) covers all the fields of engineering and science: Electrical Engineering, Mechanical Engineering, Civil Engineering, Chemical Engineering, Computer Engineering, Agricultural Engineering, Aerospace Engineering, Thermodynamics, Structural Engineering, Control Engineering, Robotics, Mechatronics, Fluid Mechanics, Nanotechnology, Simulators, Web-based Learning, Remote Laboratories, Engineering Design Methods, Education Research, Students' Satisfaction and Motivation, Global Projects, and Assessment…. And many more.
The document summarizes a numerical study that investigated the effect of distributed trailing edge suction on the aerodynamic performance of a wind turbine airfoil. Computational fluid dynamics simulations were performed on a NACA 63-415 airfoil with and without trailing edge suction at different angles of attack. The results showed that moderate levels of suction (0.5 m/s) improved the airfoil's lift-to-drag ratio by increasing maximum lift and reducing drag. Higher suction velocities (over 1 m/s) decreased aerodynamic performance by increasing drag. The optimum angle of attack was also increased from 4 degrees to 6 degrees with suction. Streamline visualizations indicated that suction effectively removed boundary layer flow
The document discusses cyclone technology for removing dust particles from air streams. It provides background on cyclone design parameters like pressure drop and collection efficiency. The optimal dimensions of cyclones are discussed, with the 2D2D design being most efficient for particles larger than 20 microns. While models can predict trends, testing is still needed due to complex flow patterns and many influencing factors. The document also reviews classical cyclone design procedures and limitations of models in accurately predicting performance metrics like number of turns and cut-point diameter.
This document outlines a dissertation proposal to study the effect of geometric parameters on the performance of an annular gas turbine combustion chamber using computational fluid dynamics (CFD). The proposal includes a literature review summarizing previous research on combustion chamber design and CFD modeling. The proposed methodology describes collecting existing dimension data, modeling the combustion chamber geometry, mesh generation, and performing CFD analysis in ANSYS Fluent to optimize performance by varying parameters like swirl angle, nozzle location and size, and hole placement and size.
This document presents research on developing an emissions prediction capability for use in conceptual aircraft engine design. A physics-based modeling approach was used consisting of 1D flow models of different combustor types, chemical reactor networks representing the combustor flowfields, and regression models. Models were developed for a single annular combustor, rich-quench-lean combustor, and lean-burn combustor. The models were implemented in NPSS and validated against test data. Regression models were also created to rapidly predict emissions for parametric studies of a CFM56-sized engine application. The new capability allows emissions predictions during early engine conceptual design when cycle parameters and architectures are varied.
The document describes an experiment to measure the uniformity of velocity in a wind tunnel. A hot wire anemometer system was used to measure the absolute, axial, vertical, and perpendicular velocity values at 6 points as a probe was moved through the test section of the wind tunnel. The results showed a range of velocities from 26.12 to 39.18 m/s, indicating a lack of uniformity. Graphs of the velocity measurements also revealed deviations. It was concluded that the non-uniform flow was likely due to the wind tunnel's contraction ratio of 9, which is below the recommended ratio of around 16 needed to achieve uniform flow. Improving the design of the contraction and suction sides could help address the issue.
IRJET- Design and Fabrication of an Open Circuit Subsonic Wind Tunnel for Edu...IRJET Journal
This document describes the design and fabrication of a low-cost subsonic wind tunnel for educational purposes. Key aspects include:
1) The wind tunnel was designed and built by students and a professor to support fluid mechanics experiments at their university on a limited budget.
2) Design considerations included achieving a test section air speed over 10m/s, compact size, ease of use, and longevity.
3) Components like the contraction cone, diffuser, test section, and flow conditioner were designed and fabricated based on guidelines from literature.
4) Experimental testing showed average air speeds in the test section of 12.9m/s, with variations within 1m/s. CFD simulation
International Journal of Engineering Research and Development (IJERD)IJERD Editor
journal publishing, how to publish research paper, Call For research paper, international journal, publishing a paper, IJERD, journal of science and technology, how to get a research paper published, publishing a paper, publishing of journal, publishing of research paper, reserach and review articles, IJERD Journal, How to publish your research paper, publish research paper, open access engineering journal, Engineering journal, Mathemetics journal, Physics journal, Chemistry journal, Computer Engineering, Computer Science journal, how to submit your paper, peer reviw journal, indexed journal, reserach and review articles, engineering journal, www.ijerd.com, research journals,
yahoo journals, bing journals, International Journal of Engineering Research and Development, google journals, hard copy of journal
International Journal of Modern Engineering Research (IJMER) is Peer reviewed, online Journal. It serves as an international archival forum of scholarly research related to engineering and science education.
International Journal of Modern Engineering Research (IJMER) covers all the fields of engineering and science: Electrical Engineering, Mechanical Engineering, Civil Engineering, Chemical Engineering, Computer Engineering, Agricultural Engineering, Aerospace Engineering, Thermodynamics, Structural Engineering, Control Engineering, Robotics, Mechatronics, Fluid Mechanics, Nanotechnology, Simulators, Web-based Learning, Remote Laboratories, Engineering Design Methods, Education Research, Students' Satisfaction and Motivation, Global Projects, and Assessment…. And many more.
The document summarizes a numerical study that investigated the effect of distributed trailing edge suction on the aerodynamic performance of a wind turbine airfoil. Computational fluid dynamics simulations were performed on a NACA 63-415 airfoil with and without trailing edge suction at different angles of attack. The results showed that moderate levels of suction (0.5 m/s) improved the airfoil's lift-to-drag ratio by increasing maximum lift and reducing drag. Higher suction velocities (over 1 m/s) decreased aerodynamic performance by increasing drag. The optimum angle of attack was also increased from 4 degrees to 6 degrees with suction. Streamline visualizations indicated that suction effectively removed boundary layer flow
The document discusses cyclone technology for removing dust particles from air streams. It provides background on cyclone design parameters like pressure drop and collection efficiency. The optimal dimensions of cyclones are discussed, with the 2D2D design being most efficient for particles larger than 20 microns. While models can predict trends, testing is still needed due to complex flow patterns and many influencing factors. The document also reviews classical cyclone design procedures and limitations of models in accurately predicting performance metrics like number of turns and cut-point diameter.
This document outlines a dissertation proposal to study the effect of geometric parameters on the performance of an annular gas turbine combustion chamber using computational fluid dynamics (CFD). The proposal includes a literature review summarizing previous research on combustion chamber design and CFD modeling. The proposed methodology describes collecting existing dimension data, modeling the combustion chamber geometry, mesh generation, and performing CFD analysis in ANSYS Fluent to optimize performance by varying parameters like swirl angle, nozzle location and size, and hole placement and size.
This document presents research on developing an emissions prediction capability for use in conceptual aircraft engine design. A physics-based modeling approach was used consisting of 1D flow models of different combustor types, chemical reactor networks representing the combustor flowfields, and regression models. Models were developed for a single annular combustor, rich-quench-lean combustor, and lean-burn combustor. The models were implemented in NPSS and validated against test data. Regression models were also created to rapidly predict emissions for parametric studies of a CFM56-sized engine application. The new capability allows emissions predictions during early engine conceptual design when cycle parameters and architectures are varied.
This document discusses cold flow analysis of a gas turbine combustor using computational fluid dynamics (CFD). CFD is used to model airflow and fuel injection without reactions to capture mixture formation. The CFD model accounts for moving geometry interactions with fluid dynamics. Cold flow simulations provide useful information on turbulence and mixing to ensure proper combustion conditions. The document outlines objectives of combustor design like satisfactory mixing and stable flow patterns with minimal losses. Numerical analysis and governing equations are presented along with experimental data and graphs showing variation in properties like temperature, pressure, and pattern factor.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
This document summarizes research using terahertz time-domain spectroscopy and tomography to sense and image within sooty flames. A bespoke high-pressure burner was designed to produce methane diffusion flames at different air co-flow rates, allowing line-of-sight THz measurements through the flames. THz time-domain spectroscopy measurements were taken of flames at various air co-flow rates from 3-12 l/min. The time delay values extracted from the THz waveforms revealed that optical density along the sensing path initially increases linearly with co-flow, then levels off after 12 l/min, indicating changes in radial temperature distribution. Varying the air co-flow provides a way to study flame properties with potential for
Comparison of Two Dispersion Models_A Bulk Petroleum Storage Terminal Case St...BREEZE Software
"This study presents a comparison of the pollutant concentration predictions from the
AERMOD and ISC air dispersion models in the context of
fugitive storage tank emissions at a bulk petroleum storage terminal."
Experimental Analysis Of Heat Transfer From Square Perforated Fins In Stagger...IJERA Editor
This project gives the experimental analysis of heat transfer over a flat surface equipped with Square perforated
pin fins in staggered arrangement in a rectangular channel. The Fin dimensions are 100mm in height & 25mm in
width. The range of Reynolds number is fixed & about 13,500– 42,000, the clearance ratio (C/H) 0, 0.33 and 1,
the inter-fin spacing ratio (Sy /D) 1.208, 1.524, 1.944 and 3.417. Sy i.e. stream wise distance is varies and Sx i.e.
span wise distance is constant. The friction factor, enhancement efficiency and heat transfer correlate in
equations with each other. Here we are comparing Square pin fins with cylindrical pin fins. Staggered
arrangement and perforation will enhance the heat transfer rate. Clearance ratio and inter-fin spacing ratio affect
on Enhancement efficiency. Both lower clearance ratio and lower inter-fin spacing ratio and comparatively lower
Reynolds number give higher thermal performance. Friction factor & Nusselt number are Key parameter which
relates with efficiency enhancement and heat transfer rate.
The document summarizes an experimental and numerical study of the effect of sweep on the three-dimensional flow downstream of axial flow fans. Three low-pressure axial flow fans were studied, with radial, forward, and backward sweep. Hot-wire anemometry was used to measure the velocity components downstream, and computational fluid dynamics (CFD) simulations using Reynolds-averaged Navier-Stokes (RANS) were performed for comparison. The results show that forward sweep decreases the radial velocity component while backward sweep increases it. The sweep also significantly influences the turbulent kinetic energy downstream of the fan.
This document summarizes a study that used computational fluid dynamics (CFD) to analyze heat transfer and flow characteristics in a solar air heater duct with ribbed surfaces. CFD simulations were performed for ducts with different rib configurations and Reynolds numbers. It was found that roughening the duct surface increased heat transfer but also increased friction losses. An optimal rib design was identified that provided maximum heat transfer enhancement with minimum pressure drop. Turbulence kinetic energy and intensity contours helped explain the increased turbulence near ribs that augmented heat transfer.
New Microsoft Office PowerPoint PresentationSudhir Shinde
This document summarizes a seminar presentation on heat transfer via jet impingement. The presentation discusses how jet impingement is used to effectively remove large amounts of heat from surfaces, such as in cooling turbine blades and electronics. It reviews factors that influence heat transfer, including nozzle diameter, jet-to-surface spacing, and Reynolds number. The experimental setup examines heat transfer characteristics of air and water jets impinging on a heated surface. Results show that lower jet diameters and spacings and higher Reynolds numbers increase heat transfer. The conclusion is that jet impingement is effective for cooling applications due to the high heat transfer coefficients that can be achieved.
This document summarizes a study that investigated the effect of Mach number on base pressure and control effectiveness in a suddenly expanded duct. The researchers conducted experiments where they varied the Mach number at the nozzle exit, nozzle pressure ratio, area ratio of the sudden expansion duct, and length-to-diameter ratio of the duct. They found that for a given area ratio, base pressure increases with Mach number. When the flow is over expanded, base pressure assumes very high values due to oblique shocks at the nozzle lip. Microjets placed at the base did not disturb the flow field in the enlarged duct.
Numerical Predictions of Enhanced Impingement Jet Cooling with Ribs and Pins ...AZOJETE UNIMAID
This document presents a numerical study of enhanced impingement jet cooling with ribs and pins on target surfaces. Computational fluid dynamics (CFD) simulations were conducted using commercial codes to predict heat transfer with different obstacle wall configurations. The obstacles investigated were ribs and rectangular pin-fins in both co-flow and cross-flow alignments. The CFD predictions showed good agreement with previous experimental results and revealed that obstacles increase turbulence but also reduce the highest thermal gradients and downstream cross-flow.
IRJET- Study of Jet Impingement Heat TransferIRJET Journal
This document reviews research on jet impingement heat transfer. It discusses the flow and heat transfer characteristics of single and multiple impinging jets. Key factors that influence heat transfer are jet Reynolds number, nozzle-to-plate spacing, jet pattern, and crossflow. The document summarizes various empirical correlations that have been developed to predict average heat transfer coefficients. It also reviews numerical studies on modeling heat transfer for multi-jet systems and discusses the effects of parameters like Reynolds number, nozzle spacing, crossflow, and jet interference.
Numerical Study Of Flue Gas Flow In A Multi Cyclone SeparatorIJERA Editor
The removal of harmful particulate matter from power plant flue gas is of critical importance to the environment and its inhabitants. The present work illustrates the use of multi-cyclone separators to remove the particulate matter from the bulk of the gas exhausted to the atmosphere. The method has potential to replace conventional systems like electrostatic precipitator due to inherent low power requirement and low maintenance. A parametric model may be employed to design the system based on the requirement of the power station. The present work describes the simulation of flue gas flow through a cyclonic separator. A Finite volume approach has been used and the pressure-velocity coupling is resolved using the SIMPLE algorithm. Discrete phase model is used to inject solid particles from inlet. In this numerical analysis a cluster of four cyclonic separators are considered. Comparisons are made between the available experimental results and the computational work for validation of the numerical models and schemes employed in the work. The separation efficiency and particle trajectories are shown and found comparable to similar cases from literature. The experimental results correlate well for the model under consideration.
A Computational Investigation of Flow Structure Within a Sinuous DuctIJERA Editor
In the present investigation the distribution of mean velocity are experimentally studied on three constant area
rectangular curved ducts with an aspect ratio of 2.4. First one is C-shape, second one is S-shape and third one
is a DS-shape duct. The experiment is carried out at mass averaged mean velocity of 40m/s for all the ducts.
The velocity distribution shows for C-duct, the bulk flow shifting from outer wall to the inner wall along the
flow passage and for S-duct, the bulk flow shifting from outer wall to the inner wall in the first half and from
inner wall to the outer wall in the second half along the flow passage of curved ducts are very instinct. Due to
the imbalance of centrifugal force and radial pressure gradient, secondary motions in the forms of counter
rotating vortices have been generated within both the curved duct. For DS-duct the velocity distributions shows
the Bulk of flow shifting from inner watt to outer wall in the first bend and third bend of the duct and outer wall
to inner wall in the second bend and forth bend of the duct along the flow passage is very instinct. Flow at end
of the DS-duct is purely uniform in nature due to non existence of secondary motion. The experimental results
then were numerically validated with the help of Fluent, which shows a good agreement between the
experimental and predicted results for all the ducts
Wall static pressure distribution due to confined impinging circular air jeteSAT Publishing House
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology.
Dr. Kei Lau is an expert in aerothermodynamics and hypersonic vehicle design. He has extensive experience with theoretical and experimental analysis techniques as well as computational fluid dynamics and thermal analysis. His work has focused on issues like boundary layer transition and thermal protection system design for programs such as the National Aero-Space Plane. High-fidelity simulation tools are needed to reduce uncertainty in hypersonic vehicle design, including computational fluid dynamics, conjugate heat transfer analysis, and finite element structural analysis.
Flow And Heat Transfer Characteristics On A Confined Slot Jet Impinging On A ...Dahiru Lawal
This document describes a study on the flow and heat transfer characteristics of a confined slot jet impinging on a constant heat flux surface. The study examines the effects of varying the jet width-to-height ratio (H/W) and Reynolds number (Re) on heat transfer properties. Numerical simulations are conducted to analyze the velocity contours, temperature distributions, Nusselt numbers, and pressure coefficients. Results show that heat transfer rate increases with higher H/W ratios and Re numbers. Flow and thermal fields also become time-dependent and asymmetric if Re exceeds a critical value. Validation of the numerical model is also performed.
Heat Transfer Enhancement through Liquid Jet ImpingementIRJET Journal
This document provides a literature review on experimental and computational studies of liquid jet impingement heat transfer. It summarizes various parameters that influence jet impingement heat transfer such as flow rate, nozzle size, inlet pressure, and working medium properties. It then reviews over 30 experimental and computational studies on topics like the effects of nozzle geometry, surface roughness, nanofluids, vortex generators, swirling jets, and more. The overall goal is to provide an overview of recent approaches to studying jet impingement heat transfer processes.
technoloTwo dimensional numerical simulation of the combined heat transfer in...ijmech
A numerical investigation was conducted to analyze the flow field and heat transfer characteristics in a vertical channel withradiation and blowing from the wall. Hydrodynamic behaviour and heat transfer results are obtained by the solution of the complete Navier–Stokesand energy equations using a control volume finite element method. Turbulent flow with "Low Reynolds Spalart-Allmaras Turbulence Model" and radiation with "Discrete Transfer Radiation Method" had been modeled. In order to have a complete survey, this article has a wide range of study in different domains including velocity profiles at different locations, turbulent viscosity, shear stress, suctioned mass flow rate in different magnitude of the input
Rayleigh number, blowing Reynoldsnumber, radiation parameter, Prandtl number, the ratio of length to width and also ratio of opening thickness to width of the channel. In addition, effects of variation in any of the above non-dimensional numbers on parameters of the flow are clearly illustrated. At the end resultants had been compared with experimental data which demonstrated that in the present study, results have a great accuracy, relative errors are very small and the curve portraits are in a great
agreement with real experiments.
This presentation investigates the hypersonic high enthalpy flow in a leading edge configuration using computational techniques, specifically using computational fluid dynamics.
Flow separation in/over a hypersonic space vehicle is an important phenomenon which occurs due to flow interaction with various geometric elements of the vehicle. This however can lead to adverse pressure gradient and localised intense heating resulting in detrimental consequences for the successful performance of the vehicle. It is therefore critical and necessary to understand the separation phenomenon and its characteristics. In the last several decades, experimental, analytical and computational techniques have been used to investigate flow separation in hypersonic flow. Despite these efforts, large gaps still remain in our understanding of the aerothermodynamics of flow separation. Typically, flow separation can be examined with simple geometric configurations representing a generic region of separated flow over a vehicle. These could range from geometries such as compression corners, flat plate with steps to blunt bodies such as cylinders and spheres. However, most of these configurations exhibit a pre-existing boundary layer prior to separation thus increasing the complexity of the interaction. A simple geometry capable of producing separation at the leading-edge without any pre-existing boundary layer is therefore considered here. This geometry was originally proposed by Chapman in 1958 for supersonic flows at high Reynolds numbers and is investigated here numerically under laminar low density hypersonic conditions using N-S and DSMC methods.
Experimental Investigation of Heat Transfer Enhancement by Using Clockwise an...ijiert bestjournal
Present Experimental work shows result obtain from experimentation of heat transfer enhancement in
circular horizontal tube by using clockwise and counterclockwise corrugated twisted tape inserts with
working fluid is air. Experiments conducted on plain circular tube with or without c-cc corrugated
twisted tube. During experiment constant heat flux and different mass flow rate condition. The c-cc
corrugated twisted tape are of same pitch and twist ratio but three different angle of rotation in
clockwise and counter clockwise direction as 30˚, 60˚, 90˚ respectively. The Reynolds no. varied from
4000 to 10000. Heat transfer coefficient and pressure drop are calculated and results are compared with
the plain tube without inserts. Finally heat transfer enhances with clockwise and counterclockwise
corrugated twisted tape inserts as compared to plain tube varied from 8 % to 44 % for various inserts.
Plain twisted tape results are also compared with the same results.
This document outlines the roles and responsibilities of an instructional design department. It describes the competencies of instructional designers which include needs assessment, applying learning theory, collaborating, designing curriculum and materials, integrating technology, and evaluating learning design. It provides an organizational chart and defines the roles of the manager, two instructional designers, and an evaluations team. Finally, it lists the equipment, software, and authoring tools needed by the department and their associated costs.
El documento describe las ventajas y desventajas de la educación a distancia y semipresencial. Algunas ventajas clave son la flexibilidad, mayor acceso y reducción de costos. Algunas desventajas incluyen la falta de interacción social y limitada retroalimentación del profesor. También describe la educación semipresencial, la cual combina el aprendizaje en línea con sesiones presenciales periódicas.
This document discusses cold flow analysis of a gas turbine combustor using computational fluid dynamics (CFD). CFD is used to model airflow and fuel injection without reactions to capture mixture formation. The CFD model accounts for moving geometry interactions with fluid dynamics. Cold flow simulations provide useful information on turbulence and mixing to ensure proper combustion conditions. The document outlines objectives of combustor design like satisfactory mixing and stable flow patterns with minimal losses. Numerical analysis and governing equations are presented along with experimental data and graphs showing variation in properties like temperature, pressure, and pattern factor.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
This document summarizes research using terahertz time-domain spectroscopy and tomography to sense and image within sooty flames. A bespoke high-pressure burner was designed to produce methane diffusion flames at different air co-flow rates, allowing line-of-sight THz measurements through the flames. THz time-domain spectroscopy measurements were taken of flames at various air co-flow rates from 3-12 l/min. The time delay values extracted from the THz waveforms revealed that optical density along the sensing path initially increases linearly with co-flow, then levels off after 12 l/min, indicating changes in radial temperature distribution. Varying the air co-flow provides a way to study flame properties with potential for
Comparison of Two Dispersion Models_A Bulk Petroleum Storage Terminal Case St...BREEZE Software
"This study presents a comparison of the pollutant concentration predictions from the
AERMOD and ISC air dispersion models in the context of
fugitive storage tank emissions at a bulk petroleum storage terminal."
Experimental Analysis Of Heat Transfer From Square Perforated Fins In Stagger...IJERA Editor
This project gives the experimental analysis of heat transfer over a flat surface equipped with Square perforated
pin fins in staggered arrangement in a rectangular channel. The Fin dimensions are 100mm in height & 25mm in
width. The range of Reynolds number is fixed & about 13,500– 42,000, the clearance ratio (C/H) 0, 0.33 and 1,
the inter-fin spacing ratio (Sy /D) 1.208, 1.524, 1.944 and 3.417. Sy i.e. stream wise distance is varies and Sx i.e.
span wise distance is constant. The friction factor, enhancement efficiency and heat transfer correlate in
equations with each other. Here we are comparing Square pin fins with cylindrical pin fins. Staggered
arrangement and perforation will enhance the heat transfer rate. Clearance ratio and inter-fin spacing ratio affect
on Enhancement efficiency. Both lower clearance ratio and lower inter-fin spacing ratio and comparatively lower
Reynolds number give higher thermal performance. Friction factor & Nusselt number are Key parameter which
relates with efficiency enhancement and heat transfer rate.
The document summarizes an experimental and numerical study of the effect of sweep on the three-dimensional flow downstream of axial flow fans. Three low-pressure axial flow fans were studied, with radial, forward, and backward sweep. Hot-wire anemometry was used to measure the velocity components downstream, and computational fluid dynamics (CFD) simulations using Reynolds-averaged Navier-Stokes (RANS) were performed for comparison. The results show that forward sweep decreases the radial velocity component while backward sweep increases it. The sweep also significantly influences the turbulent kinetic energy downstream of the fan.
This document summarizes a study that used computational fluid dynamics (CFD) to analyze heat transfer and flow characteristics in a solar air heater duct with ribbed surfaces. CFD simulations were performed for ducts with different rib configurations and Reynolds numbers. It was found that roughening the duct surface increased heat transfer but also increased friction losses. An optimal rib design was identified that provided maximum heat transfer enhancement with minimum pressure drop. Turbulence kinetic energy and intensity contours helped explain the increased turbulence near ribs that augmented heat transfer.
New Microsoft Office PowerPoint PresentationSudhir Shinde
This document summarizes a seminar presentation on heat transfer via jet impingement. The presentation discusses how jet impingement is used to effectively remove large amounts of heat from surfaces, such as in cooling turbine blades and electronics. It reviews factors that influence heat transfer, including nozzle diameter, jet-to-surface spacing, and Reynolds number. The experimental setup examines heat transfer characteristics of air and water jets impinging on a heated surface. Results show that lower jet diameters and spacings and higher Reynolds numbers increase heat transfer. The conclusion is that jet impingement is effective for cooling applications due to the high heat transfer coefficients that can be achieved.
This document summarizes a study that investigated the effect of Mach number on base pressure and control effectiveness in a suddenly expanded duct. The researchers conducted experiments where they varied the Mach number at the nozzle exit, nozzle pressure ratio, area ratio of the sudden expansion duct, and length-to-diameter ratio of the duct. They found that for a given area ratio, base pressure increases with Mach number. When the flow is over expanded, base pressure assumes very high values due to oblique shocks at the nozzle lip. Microjets placed at the base did not disturb the flow field in the enlarged duct.
Numerical Predictions of Enhanced Impingement Jet Cooling with Ribs and Pins ...AZOJETE UNIMAID
This document presents a numerical study of enhanced impingement jet cooling with ribs and pins on target surfaces. Computational fluid dynamics (CFD) simulations were conducted using commercial codes to predict heat transfer with different obstacle wall configurations. The obstacles investigated were ribs and rectangular pin-fins in both co-flow and cross-flow alignments. The CFD predictions showed good agreement with previous experimental results and revealed that obstacles increase turbulence but also reduce the highest thermal gradients and downstream cross-flow.
IRJET- Study of Jet Impingement Heat TransferIRJET Journal
This document reviews research on jet impingement heat transfer. It discusses the flow and heat transfer characteristics of single and multiple impinging jets. Key factors that influence heat transfer are jet Reynolds number, nozzle-to-plate spacing, jet pattern, and crossflow. The document summarizes various empirical correlations that have been developed to predict average heat transfer coefficients. It also reviews numerical studies on modeling heat transfer for multi-jet systems and discusses the effects of parameters like Reynolds number, nozzle spacing, crossflow, and jet interference.
Numerical Study Of Flue Gas Flow In A Multi Cyclone SeparatorIJERA Editor
The removal of harmful particulate matter from power plant flue gas is of critical importance to the environment and its inhabitants. The present work illustrates the use of multi-cyclone separators to remove the particulate matter from the bulk of the gas exhausted to the atmosphere. The method has potential to replace conventional systems like electrostatic precipitator due to inherent low power requirement and low maintenance. A parametric model may be employed to design the system based on the requirement of the power station. The present work describes the simulation of flue gas flow through a cyclonic separator. A Finite volume approach has been used and the pressure-velocity coupling is resolved using the SIMPLE algorithm. Discrete phase model is used to inject solid particles from inlet. In this numerical analysis a cluster of four cyclonic separators are considered. Comparisons are made between the available experimental results and the computational work for validation of the numerical models and schemes employed in the work. The separation efficiency and particle trajectories are shown and found comparable to similar cases from literature. The experimental results correlate well for the model under consideration.
A Computational Investigation of Flow Structure Within a Sinuous DuctIJERA Editor
In the present investigation the distribution of mean velocity are experimentally studied on three constant area
rectangular curved ducts with an aspect ratio of 2.4. First one is C-shape, second one is S-shape and third one
is a DS-shape duct. The experiment is carried out at mass averaged mean velocity of 40m/s for all the ducts.
The velocity distribution shows for C-duct, the bulk flow shifting from outer wall to the inner wall along the
flow passage and for S-duct, the bulk flow shifting from outer wall to the inner wall in the first half and from
inner wall to the outer wall in the second half along the flow passage of curved ducts are very instinct. Due to
the imbalance of centrifugal force and radial pressure gradient, secondary motions in the forms of counter
rotating vortices have been generated within both the curved duct. For DS-duct the velocity distributions shows
the Bulk of flow shifting from inner watt to outer wall in the first bend and third bend of the duct and outer wall
to inner wall in the second bend and forth bend of the duct along the flow passage is very instinct. Flow at end
of the DS-duct is purely uniform in nature due to non existence of secondary motion. The experimental results
then were numerically validated with the help of Fluent, which shows a good agreement between the
experimental and predicted results for all the ducts
Wall static pressure distribution due to confined impinging circular air jeteSAT Publishing House
IJRET : International Journal of Research in Engineering and Technology is an international peer reviewed, online journal published by eSAT Publishing House for the enhancement of research in various disciplines of Engineering and Technology. The aim and scope of the journal is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high-level learning, teaching and research in the fields of Engineering and Technology. We bring together Scientists, Academician, Field Engineers, Scholars and Students of related fields of Engineering and Technology.
Dr. Kei Lau is an expert in aerothermodynamics and hypersonic vehicle design. He has extensive experience with theoretical and experimental analysis techniques as well as computational fluid dynamics and thermal analysis. His work has focused on issues like boundary layer transition and thermal protection system design for programs such as the National Aero-Space Plane. High-fidelity simulation tools are needed to reduce uncertainty in hypersonic vehicle design, including computational fluid dynamics, conjugate heat transfer analysis, and finite element structural analysis.
Flow And Heat Transfer Characteristics On A Confined Slot Jet Impinging On A ...Dahiru Lawal
This document describes a study on the flow and heat transfer characteristics of a confined slot jet impinging on a constant heat flux surface. The study examines the effects of varying the jet width-to-height ratio (H/W) and Reynolds number (Re) on heat transfer properties. Numerical simulations are conducted to analyze the velocity contours, temperature distributions, Nusselt numbers, and pressure coefficients. Results show that heat transfer rate increases with higher H/W ratios and Re numbers. Flow and thermal fields also become time-dependent and asymmetric if Re exceeds a critical value. Validation of the numerical model is also performed.
Heat Transfer Enhancement through Liquid Jet ImpingementIRJET Journal
This document provides a literature review on experimental and computational studies of liquid jet impingement heat transfer. It summarizes various parameters that influence jet impingement heat transfer such as flow rate, nozzle size, inlet pressure, and working medium properties. It then reviews over 30 experimental and computational studies on topics like the effects of nozzle geometry, surface roughness, nanofluids, vortex generators, swirling jets, and more. The overall goal is to provide an overview of recent approaches to studying jet impingement heat transfer processes.
technoloTwo dimensional numerical simulation of the combined heat transfer in...ijmech
A numerical investigation was conducted to analyze the flow field and heat transfer characteristics in a vertical channel withradiation and blowing from the wall. Hydrodynamic behaviour and heat transfer results are obtained by the solution of the complete Navier–Stokesand energy equations using a control volume finite element method. Turbulent flow with "Low Reynolds Spalart-Allmaras Turbulence Model" and radiation with "Discrete Transfer Radiation Method" had been modeled. In order to have a complete survey, this article has a wide range of study in different domains including velocity profiles at different locations, turbulent viscosity, shear stress, suctioned mass flow rate in different magnitude of the input
Rayleigh number, blowing Reynoldsnumber, radiation parameter, Prandtl number, the ratio of length to width and also ratio of opening thickness to width of the channel. In addition, effects of variation in any of the above non-dimensional numbers on parameters of the flow are clearly illustrated. At the end resultants had been compared with experimental data which demonstrated that in the present study, results have a great accuracy, relative errors are very small and the curve portraits are in a great
agreement with real experiments.
This presentation investigates the hypersonic high enthalpy flow in a leading edge configuration using computational techniques, specifically using computational fluid dynamics.
Flow separation in/over a hypersonic space vehicle is an important phenomenon which occurs due to flow interaction with various geometric elements of the vehicle. This however can lead to adverse pressure gradient and localised intense heating resulting in detrimental consequences for the successful performance of the vehicle. It is therefore critical and necessary to understand the separation phenomenon and its characteristics. In the last several decades, experimental, analytical and computational techniques have been used to investigate flow separation in hypersonic flow. Despite these efforts, large gaps still remain in our understanding of the aerothermodynamics of flow separation. Typically, flow separation can be examined with simple geometric configurations representing a generic region of separated flow over a vehicle. These could range from geometries such as compression corners, flat plate with steps to blunt bodies such as cylinders and spheres. However, most of these configurations exhibit a pre-existing boundary layer prior to separation thus increasing the complexity of the interaction. A simple geometry capable of producing separation at the leading-edge without any pre-existing boundary layer is therefore considered here. This geometry was originally proposed by Chapman in 1958 for supersonic flows at high Reynolds numbers and is investigated here numerically under laminar low density hypersonic conditions using N-S and DSMC methods.
Experimental Investigation of Heat Transfer Enhancement by Using Clockwise an...ijiert bestjournal
Present Experimental work shows result obtain from experimentation of heat transfer enhancement in
circular horizontal tube by using clockwise and counterclockwise corrugated twisted tape inserts with
working fluid is air. Experiments conducted on plain circular tube with or without c-cc corrugated
twisted tube. During experiment constant heat flux and different mass flow rate condition. The c-cc
corrugated twisted tape are of same pitch and twist ratio but three different angle of rotation in
clockwise and counter clockwise direction as 30˚, 60˚, 90˚ respectively. The Reynolds no. varied from
4000 to 10000. Heat transfer coefficient and pressure drop are calculated and results are compared with
the plain tube without inserts. Finally heat transfer enhances with clockwise and counterclockwise
corrugated twisted tape inserts as compared to plain tube varied from 8 % to 44 % for various inserts.
Plain twisted tape results are also compared with the same results.
This document outlines the roles and responsibilities of an instructional design department. It describes the competencies of instructional designers which include needs assessment, applying learning theory, collaborating, designing curriculum and materials, integrating technology, and evaluating learning design. It provides an organizational chart and defines the roles of the manager, two instructional designers, and an evaluations team. Finally, it lists the equipment, software, and authoring tools needed by the department and their associated costs.
El documento describe las ventajas y desventajas de la educación a distancia y semipresencial. Algunas ventajas clave son la flexibilidad, mayor acceso y reducción de costos. Algunas desventajas incluyen la falta de interacción social y limitada retroalimentación del profesor. También describe la educación semipresencial, la cual combina el aprendizaje en línea con sesiones presenciales periódicas.
Este documento proporciona información sobre Gmail, uno de los servicios de correo electrónico más populares. Explica que Gmail ofrece un gran almacenamiento gratuito, herramientas de búsqueda avanzadas y funciones de personalización. También describe los pasos para crear una cuenta de Gmail, que incluyen ingresar la información personal, verificar la cuenta y completar el perfil del usuario.
Este documento presenta los resultados de un estudio sobre la Responsabilidad Familiar Corporativa en Argentina en 2013. El estudio analiza las políticas, cultura y percepciones de los empleados sobre la integración entre el trabajo y la vida familiar. Los resultados muestran que las políticas de flexibilidad del tiempo y espacio son menos comunes en Argentina que a nivel mundial, mientras que el apoyo a la familia como guarderías es similar. La mayoría de los empleados argentinos perciben que su entorno laboral dificulta u ocasionalmente dificulta la conciliación trabajo
Kenia es un país de África Oriental con costas en el Océano Índico. Su infraestructura de transporte incluye carreteras y ferrocarriles que conectan al país con sus socios comerciales cercanos. Las principales exportaciones de Kenia son té, productos hortícolas, derivados del petróleo, pescado y cemento; e importa maquinaria, derivados del petróleo y vehículos. Los principales socios comerciales de Kenia son Reino Unido, Países Bajos, Uganda, Tanzania, Estados Un
El documento describe la experiencia del IES Añaza y Proyecto Hombre sobre las adicciones al alcohol, tabaco y cannabis. Se discuten las razones a favor y en contra de cada adicción, así como la exposición a ellas y las conclusiones extraídas. También se intentan eliminar mitos comunes sobre las adicciones y se analizan los problemas que pueden desencadenar.
November-December 2009 Issue of Trendlines Magazine published by the Utah Department of Workforce Services. For more information, please visit Jobs.Utah.gov
All In One Marketing provides a service that allows businesses to communicate with customers and prospects across multiple channels including SMS, email, Facebook, and instant messengers from a single integrated dashboard. It is a two-step process of first building a contact list and then marketing to that list. The service offers features like sending automated text campaigns, appointment reminders, and mobile coupons. Pricing plans start at £99 per month.
El documento describe los conceptos básicos de un modelo de base de datos entidad-relación, incluyendo entidades, relaciones, claves primarias, y tipos de relaciones como uno a uno, uno a muchos, y muchos a muchos. Explica que una base de datos es un conjunto de información relacionada y que el modelo entidad-relación representa el mundo real mediante objetos (entidades) y las relaciones entre ellos.
El documento describe los servicios de reportes sindicados ofrecidos por Grupo Integral Regional para facilitar la toma de decisiones inmediatas de las empresas. Los reportes incluyen información sobre el tamaño y segmentación del universo de negocios, bases de datos de empresas, y diagnósticos de participación de mercado y necesidades de clientes potenciales. Los reportes se entregan de forma profesional, oportuna y a bajo costo para apoyar las estrategias y decisiones de los clientes.
Este documento presenta una política de seguridad para sistemas informáticos. Explica que la seguridad informática protege activos como software, bases de datos y archivos mediante el establecimiento de normas que minimizan riesgos a la información. También describe las amenazas internas y externas como virus, intrusos y manipulaciones maliciosas, así como técnicas para asegurar sistemas e instituciones de seguridad informática.
Este documento presenta los resultados de un estudio sobre la Responsabilidad Familiar Corporativa en empresas de Guatemala realizado por el IESE Business School. El estudio analiza las políticas, cultura y percepciones de los empleados sobre la integración entre el trabajo y la vida familiar. Los resultados muestran que las empresas en Guatemala tienen más oportunidad de mejorar en el apoyo a la conciliación laboral-familiar a través de políticas más definidas, liderazgo comprometido y una cultura que valore tanto el trabajo como la vida personal de los empleados.
Este documento describe la Responsabilidad Familiar Corporativa (RFC) y proporciona un resumen de las políticas y entornos laborales relacionados con la conciliación de la vida laboral y familiar. El objetivo es realizar un diagnóstico de la situación actual en Brasil con respecto a la integración de la vida laboral, personal y familiar de los empleados. Se analizan cuatro tipos de entornos laborales (enriquecedor, favorable, desfavorable y contaminante) y se presentan datos sobre políticas de flexibilidad del tiempo y el espacio de trabajo en Brasil
Introducción A La Orientación A Aspectos - Programador PHPJuan Belón Pérez
Este documento introduce la orientación a aspectos (POA) como una técnica para lograr la separación de preocupaciones (SoC) en el desarrollo de software. La POA separa la funcionalidad principal de un sistema de aspectos transversales como la seguridad, el rendimiento y la administración. Esto tiene beneficios como un código más fácil de entender y mantener. La POA identifica componentes funcionales y aspectos no funcionales. Luego implementa cada uno por separado antes de volver a unirlos mediante un proceso llamado "tejido
Técnicas , recursos y procedimientos de la investigacionSandy De La Ossa
Este documento presenta información sobre métodos de investigación social como encuestas, entrevistas y cuestionarios. Explica que las encuestas son una técnica para obtener datos mediante un diálogo entre el investigador y el investigado, y que su objetivo es descubrir información de una muestra de individuos. También describe brevemente los cuestionarios, entrevistas y la importancia de realizar pruebas piloto para mejorar estos instrumentos de recolección de datos.
Big data presents opportunities for companies to gain valuable insights from vast amounts of information. By analyzing big data, companies can learn more about customer preferences and behaviors which can help them improve their products and services. However, companies must ensure proper management and analysis of big data to realize its benefits while avoiding potential privacy and security risks.
The hero's journey making money doing what they love - paris - april 2014 (1)Peter de Kuster
This document introduces a travel guidebook for creative professionals seeking to build successful careers doing what they love. It discusses the challenges creative people face in the traditional business world and provides stories of creative heroes who have overcome these challenges. The guidebook aims to provide concrete tips and lessons from these heroes to help creatives develop the skills needed to turn their passions into viable careers, including how to choose the right career path, set goals, market themselves, and balance being their own boss with financial security. The overall message is that while the creative field is competitive, one can succeed by following their dreams and using the strategies of past creative heroes as inspiration and guidance.
Este documento explica la legislación y normativa que rige la Asignación de Perfeccionamiento para profesionales de la educación en Chile. Detalla los tipos de cursos que califican, cómo se calcula el porcentaje asignado, y los pasos a seguir si un municipio se niega a reconocer la asignación.
Este documento presenta el primer tema del ciclo "Hablemos de Marketing Online", que es Social Media. Explica que cada mes se dedicará a un tema específico de marketing online. Para el tema de Social Media, invita a varios bloggers expertos a dar su punto de vista a través de entrevistas y posts específicos sobre temas como qué son los social media, sus ventajas, cómo empezar a usarlos, casos de éxito y más. Además, incluye el índice de contenidos que se abordarán.
El documento presenta información sobre diferentes tipos de normas como las morales, jurídicas, sociales y deontológicas. Explica que las normas morales regulan actos internos mientras que las jurídicas establecen sanciones. Las normas sociales no implican sanciones formales pero sí reproche social. Finalmente, las normas deontológicas guían la actividad profesional de abogados.
ER Publication,
IJETR, IJMCTR,
Journals,
International Journals,
High Impact Journals,
Monthly Journal,
Good quality Journals,
Research,
Research Papers,
Research Article,
Free Journals, Open access Journals,
erpublication.org,
Engineering Journal,
Science Journals,
Design and Fabrication of Subsonic Wind TunnelIJMERJOURNAL
The document describes the design and fabrication of a subsonic wind tunnel. It discusses how wind tunnels are used to study aerodynamics of objects by moving air past stationary models. The constructed wind tunnel consists of a contraction cone, test section, and diffuser. Aerodynamic forces and drag were measured on scaled vehicle models placed in the test section. The wind tunnel was found to efficiently test aerodynamics and calculate drag, allowing more efficient vehicle design. Future work may include testing airfoils and pressure variations on obstructions.
Analysis of wings using Airfoil NACA 4412 at different angle of attackIJMER
This document summarizes wind tunnel testing of the NACA 4412 airfoil at different angles of attack. The testing was conducted to analyze lift and drag forces on the airfoil at varying angles. The results found that lift increases with angle of attack until a maximum is reached, after which drag becomes dominant and stall occurs. Graphs and tables presented in the document compare experimental pressure and friction coefficient data from the wind tunnel tests to computational fluid dynamics simulations using different turbulence models. The models were able to accurately predict flow separation locations and other characteristics.
This document summarizes a computational fluid dynamics (CFD) analysis of an exhaust silencer stack. The CFD model was used to analyze the impact of baffle perforations and sampling port location on flow patterns and emission measurements. The analysis found that velocity flow and pressure distribution were affected by the presence of porous material in the silencer baffles. Specifically, velocity was reduced and pressure drop was higher with porous baffles compared to non-porous baffles. The CFD model provides a lower cost method to evaluate design changes compared to physical testing and can help optimize baffle and port design.
IRJET-To Investigate the effect of Spinner Geometry on COP of Vortex Tube Ref...IRJET Journal
This document summarizes a research paper that investigates how changing the geometry of the spinner inside a vortex tube affects its coefficient of performance (COP) for refrigeration. The paper describes how a vortex tube works by separating compressed air into hot and cold streams. It then discusses changing the angle of the spinner notches within the vortex tube from 25 to 45 degrees and using computational fluid dynamics (CFD) software to analyze how this affects temperatures and COP. The document reviews previous literature on vortex tube experiments and analysis, and describes the methodology of using CAD software to model different spinner angles and CFD to simulate flow, temperature, and pressure within the vortex tube.
This document provides an inventory and stress analysis of microphone struts used at NASA's National Full-Scale Aerodynamics Complex (NFAC). 21 microphone struts were identified and measured. Strut airfoils were analyzed in XFLR5 to determine lift and drag coefficients. Handwritten stress analyses were performed on the struts and critical points to calculate stresses, factors of safety, and recommended maximum wind tunnel speeds. The secondary objective was to find a strut capable of safely operating at 300 knots in the 40-by-80 Foot Wind Tunnel for an upcoming test of the Tilt-Rotor Test Rig. Finite element analyses using Creo were also planned to further analyze strut stresses.
This document provides information about wind tunnels. It begins with an introduction that defines a wind tunnel as an aerodynamic device used to test how air flows around objects. It then discusses the history and present use of wind tunnels. The working principle, classifications, components, advantages, disadvantages, and calculations involved in wind tunnels are described. Conclusions state that wind tunnel results may differ from real-world conditions due to boundary layer effects. References are provided at the end.
IRJET- Design, Manufacturing and Testing of Open-Circuit Subsonic Wind Tunnel...IRJET Journal
This document provides a comprehensive review of the design, manufacturing, and testing of open-circuit subsonic wind tunnels. It discusses key components like the test section, contraction cone, diffuser, and drive system. For the settling chamber and honeycomb structure, the document recommends a length 5-10 times the diameter to reduce lateral turbulence, and notes hexagonal cells have the lowest pressure drop. It states the contraction ratio should be between 7-12 for optimum performance to eliminate axial flow fluctuations. The document also categorizes wind tunnels as open-circuit or closed-circuit, and describes classifications based on airflow speed like subsonic, transonic, supersonic, and hypersonic.
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
This document summarizes a study on optimizing the aerodynamic design of wind turbine blades using winglets. The study used computational fluid dynamics (CFD) software to model and analyze a scaled wind turbine model with and without winglets. The results showed that adding winglets to the blades reduced drag and increased lift, leading to a 1.3% increase in power production. Pointing the winglets downstream further improved performance. In conclusion, winglets show potential for improving blade efficiency but their effects on increased thrust must also be considered.
Experimental Investigations and Computational Analysis on Subsonic Wind Tunnelijtsrd
This paper disclose the entire approach to design an open circuit subsonic wind tunnel which will be used to consider the wind impact on the airfoil. The current rules and discoveries of the past research works were sought after for plan figuring of different segments of the wind tunnel. Wind speed of 26 m s have been practiced at the test territory. The wind qualities over a symmetrical airfoil are viewed as probably in a low speed wind tunnel. Tests were finished by moving the approach, from 0 to 5 degree. The stream attributes over a symmetrical airfoil are examined tentatively. The pressure distribution on the airfoil area was estimated, lift and drag force were estimated and velocity profiles were acquired. Rishabh Kumar Sahu | Saurabh Sharma | Vivek Swaroop | Vishal Kumar ""Experimental Investigations and Computational Analysis on Subsonic Wind Tunnel"" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-3 | Issue-3 , April 2019, URL: https://www.ijtsrd.com/papers/ijtsrd23511.pdf
Paper URL: https://www.ijtsrd.com/engineering/mechanical-engineering/23511/experimental-investigations-and-computational-analysis-on-subsonic-wind-tunnel/rishabh-kumar-sahu
Determination of shock losses and pressure losses in ug mine openingsSafdar Ali
This document discusses determining pressure and shock losses in underground mine openings using computational fluid dynamics (CFD) simulation techniques. It aims to calculate losses in different mine configurations using CFD and compare results to classical formulas. The document outlines the objective, scope, literature review on losses, and CFD methodology. It describes setting up simulations of common mine geometries like tunnels, bends, junctions, and shafts in Gambit meshing software and analyzing them in Fluent. Results are presented on velocity profiles and pressure losses for configurations like gradual contractions and expansions.
Determination of shock losses and pressure losses in ug mine openings (1)Safdar Ali
This document discusses the determination of shock and pressure losses in underground mine openings using computational fluid dynamics (CFD) simulation techniques. The objective is to calculate losses in different mine configurations and compare results from CFD simulations to classical formulas. The document outlines the scope of the project, literature review on losses, and describes meshing mine geometries in Gambit and performing CFD simulations in Fluent. Results are presented for simulations of tunnels, bends, junctions, contractions, expansions, shafts, and regulators. CFD-generated shock loss coefficients are found to agree reasonably well with published values, except for splits/junctions and forcing shafts, which may be due to modeling limitations. The conclusion is that 3D
Pendulum Dampers for Tall RC Chimney Subjected To WindIJERA Editor
Chimneys are a part of industrial growth in any country. Most current chimney design standards require analysis of dynamic analysis of chimney for earthquake and wind induced loads. Because of variation in dimensions of chimney along its height structural analysis such as wind oscillations have become more critical. If ductility is an important consideration in earthquake resistant design, control of deflection become critical in wind induced vibrations. Pendulum dampers are of the devices to control the deflection. In the present work pendulum dampers of different natural frequencies have been tried. The one which has the largest equivalent logarithmic decrement is found to reduce the response significantly. The response is compared with that of chimney with a tip mass. The paper discusses the dynamic analysis of 150m high RCC chimney subjected to wind. Analysis has been carried out for fixed base case.
The UCLA Rocket Project has continued developing its custom hybrid rocket engine called HyPE for the 6th Intercollegiate Rocket Engineering Competition. The HyPE uses paraffin wax and aluminum powder fuel with nitrous oxide oxidizer, and is capable of propelling a 10 pound payload to 25,000 feet. Students designed and built a carbon fiber airframe, recovery system, avionics, and ground support equipment. Aerodynamic analysis was performed to optimize the rocket's drag, and a 4.5:1 LD Haack nose cone was selected to reduce wave drag at supersonic speeds. The project involves over 30 students and aims to compete in and win the advanced category of IREC.
Diffuser in Steam Vent Silencer By Using Computational Fluid DynamicsIJERA Editor
This document summarizes a research paper that investigated the shape optimization of the pressurized inlet diffuser in a steam vent silencer using computational fluid dynamics (CFD). The researchers analyzed the pressure drop through the silencer with different hole geometries (circular, square, square extrusion) in the inlet diffuser. The results showed that square extrusion geometry had the lowest pressure drop compared to the other geometries. Therefore, the researchers concluded that optimizing the shape of the inlet diffuser to use square extrusion holes can reduce pressure drop in the steam vent silencer.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
This document describes an experimental and computational study of flow over a blunt cylinder-flare model in high supersonic flow. Wind tunnel experiments were conducted in the TST-27 and ST-15 wind tunnels at Mach numbers from 3 to 4 and angles of attack up to 20 degrees. Measurements included surface pressure distributions, flow visualization using shadowgraph and Schlieren techniques, and digital holographic interferometry to obtain density distributions in the flowfield. Computational simulations of the inviscid flow were also performed using a three-dimensional Euler solver. The goal was to provide high-quality aerodynamic data to validate computational fluid dynamics codes for simulating high-speed flows with phenomena such as shocks, separation
IRJET- Thermal Analysis on Solar Air Heater DuctIRJET Journal
This document summarizes a numerical study on the effects of transverse rectangular ribs on heat transfer properties in a solar air heater duct. Computational fluid dynamics (CFD) simulations were performed to analyze thin and square ribs arranged in single, staggered, and inline patterns. The simulations found that introducing ribs significantly increased heat transfer compared to a smooth duct. Thin ribs performed better than square ribs. Inline thin ribs produced a 1.83 times higher heat transfer coefficient than the smooth duct. Reynolds number increases led to higher Nusselt numbers for all cases. Staggered ribs had lower heat transfer than inline ribs. The study provides conclusions on rib effects and turbulence model selection for predicting solar air heater performance.
Cosa hanno in comune un mattoncino Lego e la backdoor XZ?Speck&Tech
ABSTRACT: A prima vista, un mattoncino Lego e la backdoor XZ potrebbero avere in comune il fatto di essere entrambi blocchi di costruzione, o dipendenze di progetti creativi e software. La realtà è che un mattoncino Lego e il caso della backdoor XZ hanno molto di più di tutto ciò in comune.
Partecipate alla presentazione per immergervi in una storia di interoperabilità, standard e formati aperti, per poi discutere del ruolo importante che i contributori hanno in una comunità open source sostenibile.
BIO: Sostenitrice del software libero e dei formati standard e aperti. È stata un membro attivo dei progetti Fedora e openSUSE e ha co-fondato l'Associazione LibreItalia dove è stata coinvolta in diversi eventi, migrazioni e formazione relativi a LibreOffice. In precedenza ha lavorato a migrazioni e corsi di formazione su LibreOffice per diverse amministrazioni pubbliche e privati. Da gennaio 2020 lavora in SUSE come Software Release Engineer per Uyuni e SUSE Manager e quando non segue la sua passione per i computer e per Geeko coltiva la sua curiosità per l'astronomia (da cui deriva il suo nickname deneb_alpha).
Dr. Sean Tan, Head of Data Science, Changi Airport Group
Discover how Changi Airport Group (CAG) leverages graph technologies and generative AI to revolutionize their search capabilities. This session delves into the unique search needs of CAG’s diverse passengers and customers, showcasing how graph data structures enhance the accuracy and relevance of AI-generated search results, mitigating the risk of “hallucinations” and improving the overall customer journey.
Sudheer Mechineni, Head of Application Frameworks, Standard Chartered Bank
Discover how Standard Chartered Bank harnessed the power of Neo4j to transform complex data access challenges into a dynamic, scalable graph database solution. This keynote will cover their journey from initial adoption to deploying a fully automated, enterprise-grade causal cluster, highlighting key strategies for modelling organisational changes and ensuring robust disaster recovery. Learn how these innovations have not only enhanced Standard Chartered Bank’s data infrastructure but also positioned them as pioneers in the banking sector’s adoption of graph technology.
Programming Foundation Models with DSPy - Meetup SlidesZilliz
Prompting language models is hard, while programming language models is easy. In this talk, I will discuss the state-of-the-art framework DSPy for programming foundation models with its powerful optimizers and runtime constraint system.
Communications Mining Series - Zero to Hero - Session 1DianaGray10
This session provides introduction to UiPath Communication Mining, importance and platform overview. You will acquire a good understand of the phases in Communication Mining as we go over the platform with you. Topics covered:
• Communication Mining Overview
• Why is it important?
• How can it help today’s business and the benefits
• Phases in Communication Mining
• Demo on Platform overview
• Q/A
Full-RAG: A modern architecture for hyper-personalizationZilliz
Mike Del Balso, CEO & Co-Founder at Tecton, presents "Full RAG," a novel approach to AI recommendation systems, aiming to push beyond the limitations of traditional models through a deep integration of contextual insights and real-time data, leveraging the Retrieval-Augmented Generation architecture. This talk will outline Full RAG's potential to significantly enhance personalization, address engineering challenges such as data management and model training, and introduce data enrichment with reranking as a key solution. Attendees will gain crucial insights into the importance of hyperpersonalization in AI, the capabilities of Full RAG for advanced personalization, and strategies for managing complex data integrations for deploying cutting-edge AI solutions.
HCL Notes and Domino License Cost Reduction in the World of DLAUpanagenda
Webinar Recording: https://www.panagenda.com/webinars/hcl-notes-and-domino-license-cost-reduction-in-the-world-of-dlau/
The introduction of DLAU and the CCB & CCX licensing model caused quite a stir in the HCL community. As a Notes and Domino customer, you may have faced challenges with unexpected user counts and license costs. You probably have questions on how this new licensing approach works and how to benefit from it. Most importantly, you likely have budget constraints and want to save money where possible. Don’t worry, we can help with all of this!
We’ll show you how to fix common misconfigurations that cause higher-than-expected user counts, and how to identify accounts which you can deactivate to save money. There are also frequent patterns that can cause unnecessary cost, like using a person document instead of a mail-in for shared mailboxes. We’ll provide examples and solutions for those as well. And naturally we’ll explain the new licensing model.
Join HCL Ambassador Marc Thomas in this webinar with a special guest appearance from Franz Walder. It will give you the tools and know-how to stay on top of what is going on with Domino licensing. You will be able lower your cost through an optimized configuration and keep it low going forward.
These topics will be covered
- Reducing license cost by finding and fixing misconfigurations and superfluous accounts
- How do CCB and CCX licenses really work?
- Understanding the DLAU tool and how to best utilize it
- Tips for common problem areas, like team mailboxes, functional/test users, etc
- Practical examples and best practices to implement right away
Removing Uninteresting Bytes in Software FuzzingAftab Hussain
Imagine a world where software fuzzing, the process of mutating bytes in test seeds to uncover hidden and erroneous program behaviors, becomes faster and more effective. A lot depends on the initial seeds, which can significantly dictate the trajectory of a fuzzing campaign, particularly in terms of how long it takes to uncover interesting behaviour in your code. We introduce DIAR, a technique designed to speedup fuzzing campaigns by pinpointing and eliminating those uninteresting bytes in the seeds. Picture this: instead of wasting valuable resources on meaningless mutations in large, bloated seeds, DIAR removes the unnecessary bytes, streamlining the entire process.
In this work, we equipped AFL, a popular fuzzer, with DIAR and examined two critical Linux libraries -- Libxml's xmllint, a tool for parsing xml documents, and Binutil's readelf, an essential debugging and security analysis command-line tool used to display detailed information about ELF (Executable and Linkable Format). Our preliminary results show that AFL+DIAR does not only discover new paths more quickly but also achieves higher coverage overall. This work thus showcases how starting with lean and optimized seeds can lead to faster, more comprehensive fuzzing campaigns -- and DIAR helps you find such seeds.
- These are slides of the talk given at IEEE International Conference on Software Testing Verification and Validation Workshop, ICSTW 2022.
Unlocking Productivity: Leveraging the Potential of Copilot in Microsoft 365, a presentation by Christoforos Vlachos, Senior Solutions Manager – Modern Workplace, Uni Systems
TrustArc Webinar - 2024 Global Privacy SurveyTrustArc
How does your privacy program stack up against your peers? What challenges are privacy teams tackling and prioritizing in 2024?
In the fifth annual Global Privacy Benchmarks Survey, we asked over 1,800 global privacy professionals and business executives to share their perspectives on the current state of privacy inside and outside of their organizations. This year’s report focused on emerging areas of importance for privacy and compliance professionals, including considerations and implications of Artificial Intelligence (AI) technologies, building brand trust, and different approaches for achieving higher privacy competence scores.
See how organizational priorities and strategic approaches to data security and privacy are evolving around the globe.
This webinar will review:
- The top 10 privacy insights from the fifth annual Global Privacy Benchmarks Survey
- The top challenges for privacy leaders, practitioners, and organizations in 2024
- Key themes to consider in developing and maintaining your privacy program
Maruthi Prithivirajan, Head of ASEAN & IN Solution Architecture, Neo4j
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UiPath Test Automation using UiPath Test Suite series, part 5DianaGray10
Welcome to UiPath Test Automation using UiPath Test Suite series part 5. In this session, we will cover CI/CD with devops.
Topics covered:
CI/CD with in UiPath
End-to-end overview of CI/CD pipeline with Azure devops
Speaker:
Lyndsey Byblow, Test Suite Sales Engineer @ UiPath, Inc.
UiPath Test Automation using UiPath Test Suite series, part 5
Bb4301290299
1. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 4, Issue 3( Version 1), March 2014, pp.290-299
www.ijera.com 290 | P a g e
Survey of Uniformity of Pressure Profile in Wind Tunnel by
Using Hot Wire Annometer Systems
Rao Yerrapragada. K.S.S1*,
S.N.Ch.Dattu .V2*,
Dr. B.Balakrishna3*
1*
Aditya Engineering College, Associate Professor in Department of Mechanical Engineering, Andhra Pradesh.
2*
Pragati Engineering College, Associate Professor in Department of Mechanical Engineering, Andhra Pradesh.
3*JNTU KAKINADA, Professor in Department of Mechanical Engineering, Andhra Pradesh
ABSTRACT
The purpose of this research work is to investigate experimentally and computationally the uniformity of
velocity profile in wind tunnel. A wind tunnel is an instrument used to examine the stream lines and forces that
are induced as the fluid flows past a fully submerged body. The uni-insta’s wind tunnel (300 mm*300 mm) has
been designed to give a large working section for the purpose of being able to layout substantial site models.
The tunnel has a built in boundary layer simulation system that allows good simulation of the atmospheric
velocity gradients. The tunnel is built around a sectionalized wooden frame work incorporating exterior grade
plywood panels in the settling length and working section, clad in laminate on the side elevation for ease of
maintenance. A bell mount entry incorporated is followed by a smooth settling length chamber comprising of
well graded honey comb network fine mesh. The side panels of the working section are transparent acrylic
cover, to gives a large viewing area .Additional matt back side panels gives photographic construct to smoke
trails. The top panel of the working section is removable in order to fix the models.
Keywords: - uni-insta’s wind tunnel, acrylic cover, stream lines.
I. BACKGROUND
In 1941 the US constructed one of the
largest wind tunnels at that time at Wright Field in
Dayton, Ohio. This wind tunnel starts at 45 feet (14
m) and narrows to 20 feet (6.1 m) in diameter. Two
40-foot (12 m) fans were driven by a 40,000 H.P
electric motor. Large scale aircraft models could be
tested at air speeds of 400 mph (640 km/h).[5] The
wind tunnel used by German scientists at
Peenemünde prior to and during WWII is an
interesting example of the difficulties associated with
extending the useful range of large wind tunnels. It
used some large natural caves which were increased
in size by excavation and then sealed to store large
volumes of air which could then be routed through
the wind tunnels. This innovative approach allowed
lab research in high-speed regimes and greatly
accelerated the rate of advance of Germany's
aeronautical engineering efforts. By the end of the
war, Germany had at least three different supersonic
wind tunnels, with one capable of Mach 4.4 (heated)
airflows. [4]
By the end of World War Two, the US had
built eight new wind tunnels, including the largest
one in the world at Moffett Field near Sunnyvale,
California, which was designed to test full size
aircraft at speeds of less than 250 mph[7] and a
vertical wind tunnel at Wright Field, Ohio, where the
wind stream is upwards for the testing of models in
spin situations and the concepts and engineering
designs for the first primitive helicopters flown in the
US.[5] Later research into airflows near or above the
speed of sound used a related approach. Metal
pressure chambers were used to store high-pressure
air which was then accelerated through a nozzle
designed to provide supersonic flow. The observation
or instrumentation chamber ("test section") was then
placed at the proper location in the throat or nozzle
for the desired airspeed. For limited applications,
Computational fluid dynamics (CFD) can increase or
possibly replace the use of wind tunnels. For
example, the experimental rocket plane Space Ship
One was designed without any use of wind tunnels.
However, on one test, flight threads were attached to
the surface of the wings, performing a wind tunnel
type of test during an actual flight in order to refine
the computational model. Where external turbulent
flow is present, CFD is not practical due to
limitations in present day computing resources. For
example, an area that is still much too complex for
the use of CFD is determining the effects of flow on
and around structures, bridges, terrain, etc. The most
effective way to simulative external turbulent flow is
through the use of a boundary layer wind tunnel.
There are many applications for boundary layer wind
tunnel modeling. For example, understanding the
impact of wind on high-rise buildings, factories,
bridges, etc. can help building designers construct a
structure that stands up to wind effects in the most
efficient manner possible. Another significant
RESEARCH ARTICLE OPEN ACCESS
2. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 4, Issue 3( Version 1), March 2014, pp.290-299
www.ijera.com 291 | P a g e
application for boundary layer wind tunnel modeling
is for understanding exhaust gas dispersion patterns
for hospitals, laboratories, and other emitting sources.
Other examples of boundary layer wind tunnel
applications are assessments of pedestrian comfort
and snow drifting. Wind tunnel modeling is accepted
as a method for aiding in Green building design. For
instance, the use of boundary layer wind tunnel
modeling can be used as a credit for Leadership in
Energy and Environmental Design (LEED)
certification through the U.S. Green Building
Council. Wind tunnel tests in a boundary layer wind
tunnel allow for the natural drag of the Earth's surface
to be simulated. For accuracy, it is important to
simulate the mean wind speed profile and turbulence
effects within the atmospheric boundary layer.
Most codes and standards recognize that
wind tunnel testing can produce reliable information
for designers, especially when their projects are in
complex terrain or on exposed sites. In the USA
many wind tunnels have been decommissioned in the
last 20 years, including some historic facilities.
Pressure is brought to bear on remaining wind
tunnels due to declining or erratic usage, high
electricity costs, and in some cases the high value of
the real estate upon which the facility sits. On the
other hand CFD validation still requires wind-tunnel
data, and this is likely to be the case for the
foreseeable future. Studies have been done and others
are under way to assess future military and
commercial wind tunnel needs, but the outcome
remains uncertain.[6] More recently an increasing use
of jet-powered, instrumented unmanned vehicles
[“research drones”] has replaced some of the
traditional uses of wind tunnels.[7]
II. OPERATION OF WIND TUNNEL
Mount the model as per requirements.
Calibrate the strain gauge balance to indicate an
initial value of life force = 25kg, drag force =
2kg.Connect the pressure tapings to the manometer
board and note the angle of incidence or angle of
attack and set the smoke generator for operation.
Then start the axial flow fan by switching on the
starter switch. Note down the differential manometer
readings, to calculate the free stream velocity
V=C√2gh. Adjust the side window opening by
operating the handle connected to it. Note the
readings of the simple u-tube manometer which is
connected to the pressure tapings. Repeat the
procedure by adjusting the velocity and also for
different angles of incidence.
III. LITERAL SURVEY
According to E.G.Tulapurkara, assistant
professor in IIT (Madras) experimental investigation
of morels method for wind tunnel contraction the
following thesis were made for improve the design of
a good wind tunnel. The contraction on the nozzle is
an important component of a wind tunnel. As the
flow passes through the contraction it accelerates and
this results in a reduction of non-uniformity and
turbulence level of the stream. In practical
contractions, which are of finite length, one finds that
adverse pressure gradients are present at the ends of
the contraction (Bradshaw and Pankhurst, 1964). The
axial velocity is higher than the velocity near the wall
at the entry to the contraction and at the exit the
velocity near the wall (i.e.; outside the boundary
layer) is higher than that on the axis.
Thus for a good performance nozzle contour
should give low adverse pressure gradients at the
ends of contraction so that no separation of flow
takes place, the boundary layer thickness at the exit
should be small and non-uniformity in the velocity
distribution at the exit must be small.. A good
contour should achieve these with a small length to
upstream diameter (D1) ratio nearly fifteen methods
to obtain the shape of contraction. Bradshaw and
Pankhurst (1964) recommended a contraction ratio of
12 for a good low turbulence wind tunnel. However,
many wind tunnels in common use have smaller
contraction ratios of the order of 4.Hence
contractions with area ratio of 12 and T2 i.e., 3.434
are chosen for the present investigation. The diameter
of the settling chamber ahead of the contraction is
250mm.Velocity in settling chamber is 4m/sec
.Hence the value of Cpl. Based on experience of
Tulapukara (1980) and the recommendation of morel
(1975) an acceptable value for the exit no uniformity
is chosen as 2%. This requires the CPC to be less
than 0.057.A value of 0.005 for Cpc is chosen. These
values of CPL and CPC give the X=0.537 and
L/D1=0.858 for C=12 and X=0.332 and L/D1=0.858.
We get D2 equal to 72.17mm and 134.32m similarly
experimental setup and technique. The velocity in
settling chamber is 4m/s. This would be nearly the
settling chamber velocity is most of wind tunnels
with test section speed between 50 to 60 m/s and
contraction ratio between 12 to 16. The velocity
distribution at ends of contraction ratio and along the
axis is obtained from measurements of total pressure
and static pressure using PILIOL and static tubes.
Micrometer FC012 made by Furness control LTD of
UK are used for pressure tubes. Typical readings of
manometer during velocity measurement near the
inlet and exit were 1.3 0.5. The velocity distribution
at the ends and distribution of axial velocity and wall
velocity along the contraction are shown and
C=3.464 respectively R1 and R2 in these figures are
the radii of contraction at inlet and exit.
3. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
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IV. HOTWIRE ANENOMETER
SYSTEM
The turbulence measurement in the
boundary layer and in the wake region was carried
out using the hot wire anemometer. The hot wire
anemometer system consists of the following
modules. 56C01 Constant Temperature Anemometer
(Two No’s) , 56C17 Bridge (Two No’s), 56N21
linearizer (Two No’s) , 56N20 signal conditioner
(Two No’s) , 56N23, Analog Processer Unit, 56N22
Mean Value Unit , 56N25 RMS Unit.
V. PRESSURE MEASUREMENT
The transverse mechanism was ended upon
the test section of the tunnel. The probe was
tightened to the transverse mechanism and introduced
vertically into the Test section of the wind tunnel.
Five hose connections were made between probe and
the manometer. All leakages in the wind tunnel were
checked and sealed. The start button was pushed on
and the following parameters were entered into
record by transferring the probe from 5mm at the top
of the test section of wind tunnel to 300 mm bottom
of test section in 6 steps.
TABULAR COLUMN:
Distance
of
Probe
Traversed
( Y)
mm
Pressure
P1
In
Mega
bars
(mbar)
Pressure
P2
In
Mega
bars
(mbar)
Pressure
P3
In
Mega
bars
(mbar)
Pressure
P4
In
Mega
bars
(mbar)
Pressure
P5
In
Mega
bars
(mbar)
Total
Pressure
(PT )In
Mega
bars
( mbar)
Static
Pressure
(Ps) In
Mega
bars
(mbar)
5 -32.5 -45.6 -45.6 -34.2 -33 -32.45 -32.39
61 -32.4 -46.5 -46.5 -34.3 -32.7 -32.39 -32.35
122 -33 -46.3 -46.3 -34.3 -32.6 -32.9 -32.9
183 -32.3 -46.6 -46.6 -34 -32.8 -32.89 -32.8
244 -31.9 -44.3 -44.3 -33.8 -32.3 -31.89 -31.84
300 -42.6 -44.1 -44.1 -43.6 -43.4 -42.6 -42.53
Table No: 1
Figure No: 1 LINE SKETCH OF A WIND TUNNEL
4. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
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Figure No: 2 EXPERIMENTAL SET UP
Figure No : 3 TEST FOR FINDING THE TUNNEL SPEED
Figure No 4: VELOCITY DISTRIBUTION CURVE
5. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
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VI. RESULTS & GRAPHS
Graph 1 : Average P1 = -34.12 mbar
Average P2 = -45.57 m bar
Graph2 : Average P1 = -34.12 m bar
Average P3 = -45.57 m bar
Graph3 : Average P1 = -34.12 m bar
Average P4 = -35.7 m bar
Graph4 : Average P1 = -34.12 m bar
Average P5 = -34.47 m bar
Graph5 : Average P2 = - 45.57 m bar
Average P3 = - 45.57 m bar
6. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 4, Issue 3( Version 1), March 2014, pp.290-299
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Graph6 : Average P2 = - 45.57 m bar
Average P4 = - 35.7 m bar
Graph7 : Average P2 = - 45.57 m bar
Average P5 = - 34.47 m bar
Graph8 : Average P3 = - 45.57 m bar
Average P4 = - 35.7 m bar
Graph9 : Average P3 = - 45.57 m bar
Average P5 = - 34.47 m bar
Graph10 : Average P4 = - 35.7 m bar
Average P5 = - 34.47 m bar
Graph11 : Average P1 = - 34.12 m bar
Avg Total Pressure( PT) = - 34.18 m bar
7. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 4, Issue 3( Version 1), March 2014, pp.290-299
www.ijera.com 296 | P a g e
Graph12 : Average P2 = - 45.57 m bar
Avg Total Pressure ( PT) = - 34.18 m bar
Graph13 : Average P3 = - 45.57 m bar
Avg Total Pressure ( PT) = - 34.18 m bar
Graph14 : Average P4 = -35.7 m bar
Avg Total Pressure ( PT) = - 34.18 m bar
Graph15 : Average P5 = - 34. 47 m bar
Avg Total Pressure ( PT) = -34.18 m bar
Graph16 : Average P1 = - 34.12 m bar
Avg Static Pressure ( PS) = - 34.13 m bar
Graph17 : Average P2 = -45.57 m bar
Avg Static Pressure ( PS) = - 34.13 m bar
8. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 4, Issue 3( Version 1), March 2014, pp.290-299
www.ijera.com 297 | P a g e
Graph18 : Average P3 = - 45.57 m bar
Avg Static Pressure ( PS) = - 34.13 m bar
Graph19 : Average P4 = -35.7 m bar
Avg Static Pressure ( PS) = -34.13 m bar
Graph20 : Average P5 = - 34.47 m bar
Avg Static Pressure ( PS) = -34.13 m bar
Graph21 : Average P1 = - 34.12 m bar
Avg Distance of Probe = 152.5 mm
Graph22 : Average P2 = - 45.57 m bar
Avg Distance of Probe = 152.5 mm
Graph23 : Average P3 = - 45.57 m bar
Avg Distance of Probe = 152.5 mm
9. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 4, Issue 3( Version 1), March 2014, pp.290-299
www.ijera.com 298 | P a g e
Graph24 : Average P4 = - 35.7 m bar
Avg Distance of Probe = 152.5 mm
Graph25 : Average P5 = - 34.47 m bar
Avg Distance of Probe = 152.5 mm
Graph26 : Average PT = - 34.18 m bar
Avg Distance of Probe = 152.5 mm
Graph27 : Average PS = - 34.13 m bar
Avg Distance of Probe = 152.5 mm
VII. CONCLUSION
We find the average actual static pressure
value is -34. 13 m bar and average total pressure
value is – 34.mbar. The pressure variations at
poistions P2 & P3 are identical. Similarly at postions
P1, P4, P5 found small marigianl changes. We
analyze that the pressue distribution of fluid is
uniform. We can see clear picture of deviation in the
graphs plotted as Pressure and its components Vs. the
transverse distance of the probe in the test section of
the wind tunnel.
VIII. REASON FOR NONUNIFORMITY
FLOW OF FLUID
The reason behind is may be due to the poor
design of the wind tunnel section side. The contact
ratio must be around 16 for to get a uniform flow.
But the contact ratio our wind tunnel is around 9.
i.e., a1 = 900×900 mm, a2 = 300×300 mm. The
contact ratio = a1/a2 = 9 which is below the required.
It is also due to the poor design of the suction side.
REFERENCES
[1] Bossel. H.H. 1969 “Computations of
Axisymmetric Contractions,” AIAA Journal
Volume 7 no.10 PP 2017-2020.
[2] Bradshaw. P & Pankhurust.R.C. 1964, “The
Design of Low Speed Wind Tunnels”,
Progress in Aeronautical Sciences Volume
5. Kuchenmann.D and Sterne. L.H.G
Editors Pergamum Press PP 1-69.
[3] Chmiclewski, GE 1974, “Boundary Layer
Consideration in design of Aerodynamic
10. R Yerrapragada. K.S.S et al Int. Journal of Engineering Research and Applications www.ijera.com
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Contractions”, Journal of Air Craft Volume
11 No 8 PP 435-438.
[4] Kiein A. Ramjee. V & Venkataramani, K.S
1973, “Ann Experimental Study of Subsonic
Flow in the axisymmetric contractions”,
Flow volume 21 no 9 PP 312-320.
[5] Morel T 1975 comprehensive Design of
Axisymmetric Wind Tunnel Contractions”
ASME JOURNAL OF FLUID
ENGINEERING, Volume 97 No2 225-233.
[6] Startford B.S 1959.The Prediction of
Separation of Fluid Mechanics, Volume Part
1 PP 1-16
[7] Thwaltes B 1946, on Design of Contraction
for Wind Tunnels, Aeronautical Research
council, London R SM 2278.