FM-Basics Topics Wise Solutions | Q & A | Flight Mechanics | GATE AerospaceAge of Aerospace
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For Video Lecture of this presentation: https://youtu.be/XNsIdHUx7q8
The topics covered in this session are, Airplane (fixed wing aircraft) configurations and various parts of airplane. A detailed list of airplane configuration is discussed with general insight about airplane parts.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
Pressure Altitude | Flight Mechanics | GATE AerospaceAge of Aerospace
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For Video Lecture of this presentation: https://youtu.be/yO0IPxVZmwE
The topics covered in this session are pressure, density and temperature altitude. The practical significance of pressure altitude is discussed along with a real case example. An alternative method is also briefed
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
SSA Convention 04, Eta Biter presentation by Dick ButlerGlider Pilot
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The document summarizes four phases of modifications made to the ASW22DB glider between 1998 and 2003 to improve performance:
Phase I involved reducing the horizontal tail area by 30% for improved drag. Phase II modified the wing airfoil profile for 7.5% lower skin friction drag. Phase III included a new vertical stabilizer and retractable tail wheel for reduced drag. Phase IV was a new outboard wing airfoil, increased span to 28m, and internal airflow improvements for lower drag. Overall the project achieved anticipated gains of 9-11% in best L/D and high speed performance.
Angle of Attack | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
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Question Analysis, Book Reference, Important Concepts, and topic wise Solutions for the topic "Angle of Attack" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
For Video Lecture of this presentation: https://youtu.be/NAjezfbWh4Y
The topics covered in this session are, drag, categories of drag, drag polar equation and drag polar graph, drag polar derivation, induced drag coefficient.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
The document presents a computational fluid dynamics analysis of flow over NACA airfoils using ANSYS Fluent. It describes modeling NACA-4412, NACA-6409, and NACA-0012 airfoils, applying boundary conditions, and analyzing lift, drag, velocity and pressure distributions. The analysis found that NACA-4412 had a higher lift-to-drag ratio than NACA-6409. Additionally, increasing the angle of attack was found to initially increase lift and drag coefficients until a certain point, after which lift decreased while drag continued increasing.
This master's thesis investigates highly loaded transonic fans through aerodynamic and aeroelastic simulations using ANSYS and ABAQUS. It consists of two parts: the first validates simulation results like modal and stress analysis against experimental data from a NASA technical paper on a two-stage fan. The second part of the thesis, under the FanTip project sponsored by German government agencies, aims to optimize jet engine fan design through aeroelastic simulations verified by wind tunnel tests, applying a traveling wave mode approach to determine flutter using ANSYS CFX and Calculix. Simulation results for the fan, outlet guide vanes, and engine blades are also compared to fan performance curves.
Angle of attack | Flight Mechanics | GATE AerospaceAge of Aerospace
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This document provides an overview of flight mechanics topics including angle of attack. It discusses the angle of attack (AOA) as the angle between the relative wind and chord line of an airfoil. Greater AOA results in greater lift but also greater drag. Higher AOA variation can cause stall from loss of lift. It recommends visualizing AOA effects using NASA's FoilSim tool. The document also outlines core topics like aircraft configurations, flight instruments, aerodynamic forces, airplane performance, stability, and dynamic stability to be covered.
The document summarizes the evolution of the ASW22DB glider through four phases from 1998 to 2003. Phase I involved building the ASW22BL with a smaller horizontal tail. Phase II modified the wing airfoil. Phase III included a new vertical stabilizer and retractable tail wheel. Phase IV added a new outboard airfoil profile, increased the span to 28m, and improved internal airflow. Performance gains anticipated included up to 11% at high speeds and improved climb. Flight tests verified the theoretical calculations and aerodynamic modifications. The completed glider met expectations by winning national competitions.
SSA 2012—Developments at Schempp-HirthGlider Pilot
Ìý
The document summarizes developments from Arcus and Quintus, two-seater and open class sailplanes respectively. For Arcus, preliminary considerations focused on comparable performance to reference sailplanes. Its design involved optimizing the airfoil, wing geometry, winglets, and aeroelastic properties. The first mold was begun in January 2009. Flight tests found it agile with good maneuverability. The Arcus M and E models are also introduced. For Quintus, the goal was an innovative open class self-launch sailplane with a high wingloading range for competition but also easy handling for other flights. Its wing was resized for lower weight but higher loading with water ballast. Both sailplanes went through prototy
This document summarizes the calibration of a subsonic wind tunnel. Calibration establishes the reliability and accuracy of measurements by comparing the wind tunnel's measurements to a standard. The specifications of the wind tunnel are provided, including a test section size of 600x600x2000 mm and maximum test section velocity of 50 m/s. The calibration procedure involves using a pitot tube connected to a manometer to measure total and static pressure at different fan speeds. These measurements are used to calculate flow velocity and plot a calibration chart comparing flow velocity to motor speed with less than 3% error.
The document analyzes the aerodynamic performance of a NACA0012 airfoil at various angles of attack using computational fluid dynamics (CFD). The study uses Ansys-Fluent to simulate air flow over the airfoil at angles of 4, 6, 8, and 10 degrees with a Reynolds number of 106. The results show increasing lift and drag coefficients with higher angles of attack. Velocity contours indicate higher speeds over the airfoil's upper surface, while pressure contours show lower pressure. Comparison to experimental data finds good agreement, validating CFD as a method for analyzing airfoil performance.
The document discusses surface stresses in gear teeth. It explains that gear teeth experience dynamic Hertzian contact stresses from rolling and sliding contact at their interface. It also describes Buckingham's analysis which modeled gear teeth as cylinders in rolling contact. Several factors that influence surface stresses are defined, including tangential load, pitch diameter, face width, surface geometry, elastic properties, and surface finish. An example calculation is presented to analyze surface stresses in a 3-gear spur gear train. Material strength is also discussed, including bending and surface fatigue strength data from AGMA and factors to adjust for life and temperature.
Design Analysis Of Uav (Unmanned Air Vehicle) Using NACA 0012 Aerofoil ProfileDr. Bhuiyan S. M. Ebna Hai
Ìý
This research work is concerned with the application of conceptual design of Unmanned Air Vehicle (UAV). UAV is used for surveillance and reconnaissance to serve for the defense as well as national security and intelligence purpose. Here NACA 0012 aerofoil profile is used to design UAV by using CFD (Computational Fluid Dynamics) software. The aim of this research is to investigate the flow patterns and determine the aerodynamic characteristics of NACA 0012 profile by varying the angle of attack and Reynolds Number numerically. The research is carried out with symmetric aerofoil with the chord length of 0.1m. The research work explained different aerodynamic characteristics like lift force and drag force, lift and drag coefficient, pressure distribution over aerofoil etc.
This document contains a lift calculation sheet for a crane job. It provides details of the crane configuration including crane type, boom length, jib type and length. It lists the weights of the crane, load, slings and other equipment. It calculates the total weight of the lift and confirms the lift is safe based on the crane's chart capacity at the actual pick radius.
A simplified nozzle ring CAD model was meshed and evaluated in ANSYS Mechanical to optimize the mesh for geometry and effectiveness. A representation of the European Transient Cycle was created to apply time-varied loads from Ricardo WAVE simulations. Four nozzle ring concepts were evaluated in ANSYS Mechanical to find equivalent stress and fatigue life, with all concepts showing stresses within the endurance limit of steel and practically infinite life with a good safety factor.
Thermo problems (cascade refrigeration cycle ) mohammad usman
Ìý
This document outlines a semester project for six students at Wah Engineering College, University of Wah. The project will cover topics including turbines, re-heaters, cascade refrigeration systems, and heat exchangers. It lists the group members and assumptions made. It also includes a sample problem solving a cascade refrigeration system, showing process points, temperatures, pressures, enthalpies and entropies. Questions are presented at the end for the students to answer as part of their project.
Analysis of wings using Airfoil NACA 4412 at different angle of attackIJMER
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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.
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil A...CrimsonPublishersRDMS
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Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil Aerodynamic Performance by Najdat Nashat Abdulla* in Crimson Publishers: Peer Reviewed Material Science Journals
This document outlines the topics that will be covered in an aviation course, including electric aircraft systems, aircraft maintenance, batteries, aerodynamics, flight maneuvers, airspace, weather, maps, regulations, mission planning, safety management, and human factors. The course appears designed to teach students about remotely piloted aircraft systems. It will cover essential aeronautical knowledge on topics like flight principles, meteorology, navigation, and aviation rules and safety.
Jay Ryan R. Santos has experience designing various types of industrial structures including pipe racks, equipment structures, shelters, table tops, modular structures, vessel foundations, tank foundations, and mining equipment foundations. He has expertise in load calculations, steel and concrete design, lifting analysis, transportation analysis, and seismic analysis of industrial structures.
Turning Moment Diagram and Flywheel (TOM)Swagatika Pal
Ìý
This document discusses turning moment diagrams and flywheels. It explains that a turning moment diagram is a graphical representation of the torque on the crankshaft at different crank angles. It shows the torque is highest at 90 degrees and lowest at 0 and 180 degrees. The area under the curve represents the work done per revolution. A flywheel stores energy when torque is high and releases it when torque is low, reducing fluctuations in speed. The ratio of maximum speed variation to mean speed is called the coefficient of fluctuation of speed. A flywheel controls speed variations caused by uneven engine torque over each operating cycle.
Current Problem
No simple system exists to measure forces exerted on crane rails
Forces are currently only analyzed through theory
Very difficult to accurately predict lateral and vertical forces hence
support designs may be inadequate
A comparative flow analysis of naca 6409 and naca 4412 aerofoileSAT Publishing House
Ìý
This document analyzes and compares the flow properties of two airfoil profiles, the NACA 6409 and NACA 4412, using computational fluid dynamics (CFD) modeling in ANSYS. The analysis examines pressure distribution, lift and drag coefficients at varying angles of attack. The NACA 4412 was found to have better lift-to-drag ratio performance and is more efficient for practical applications compared to the NACA 6409.
IRJET-Subsonic Flow Study and Analysis on Rotating Cylinder AirfoilIRJET Journal
Ìý
This document presents a study on modifying the lift characteristics of a conventional symmetrical airfoil (NACA 0012) by adding a rotating cylinder. A numerical analysis and computational fluid dynamics simulation were conducted. Two cases were considered: a cylinder with 13mm diameter located at the 0.125 chord point, and a 15mm cylinder at the 0.25 chord point. The presence of a rotating cylinder was found to significantly increase the airfoil's lift at zero angle of attack through momentum injection, by up to 100%. It also delayed stall characteristics. The document outlines the methodology, including the airfoil geometry, range of air velocities and cylinder rotation speeds studied, and equations used to model static and total pressure.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
The document discusses modeling the behavior of thermoplastics in ANSYS. It describes the stress-strain behavior of thermoplastics under different loading conditions such as uniaxial tension, loading-unloading, creep, and relaxation. It also lists several material models in ANSYS that can be used to model different thermoplastic behaviors, such as elastic-plastic, hyperelastic, viscoelastic, and viscoplastic models. It provides guidance on choosing the appropriate material model based on the available experimental data, operating loading conditions, and simulation objectives.
The document summarizes the evolution of the ASW22DB glider through four phases from 1998 to 2003. Phase I involved building the ASW22BL with a smaller horizontal tail. Phase II modified the wing airfoil. Phase III included a new vertical stabilizer and retractable tail wheel. Phase IV added a new outboard airfoil profile, increased the span to 28m, and improved internal airflow. Performance gains anticipated included up to 11% at high speeds and improved climb. Flight tests verified the theoretical calculations and aerodynamic modifications. The completed glider met expectations by winning national competitions.
SSA 2012—Developments at Schempp-HirthGlider Pilot
Ìý
The document summarizes developments from Arcus and Quintus, two-seater and open class sailplanes respectively. For Arcus, preliminary considerations focused on comparable performance to reference sailplanes. Its design involved optimizing the airfoil, wing geometry, winglets, and aeroelastic properties. The first mold was begun in January 2009. Flight tests found it agile with good maneuverability. The Arcus M and E models are also introduced. For Quintus, the goal was an innovative open class self-launch sailplane with a high wingloading range for competition but also easy handling for other flights. Its wing was resized for lower weight but higher loading with water ballast. Both sailplanes went through prototy
This document summarizes the calibration of a subsonic wind tunnel. Calibration establishes the reliability and accuracy of measurements by comparing the wind tunnel's measurements to a standard. The specifications of the wind tunnel are provided, including a test section size of 600x600x2000 mm and maximum test section velocity of 50 m/s. The calibration procedure involves using a pitot tube connected to a manometer to measure total and static pressure at different fan speeds. These measurements are used to calculate flow velocity and plot a calibration chart comparing flow velocity to motor speed with less than 3% error.
The document analyzes the aerodynamic performance of a NACA0012 airfoil at various angles of attack using computational fluid dynamics (CFD). The study uses Ansys-Fluent to simulate air flow over the airfoil at angles of 4, 6, 8, and 10 degrees with a Reynolds number of 106. The results show increasing lift and drag coefficients with higher angles of attack. Velocity contours indicate higher speeds over the airfoil's upper surface, while pressure contours show lower pressure. Comparison to experimental data finds good agreement, validating CFD as a method for analyzing airfoil performance.
The document discusses surface stresses in gear teeth. It explains that gear teeth experience dynamic Hertzian contact stresses from rolling and sliding contact at their interface. It also describes Buckingham's analysis which modeled gear teeth as cylinders in rolling contact. Several factors that influence surface stresses are defined, including tangential load, pitch diameter, face width, surface geometry, elastic properties, and surface finish. An example calculation is presented to analyze surface stresses in a 3-gear spur gear train. Material strength is also discussed, including bending and surface fatigue strength data from AGMA and factors to adjust for life and temperature.
Design Analysis Of Uav (Unmanned Air Vehicle) Using NACA 0012 Aerofoil ProfileDr. Bhuiyan S. M. Ebna Hai
Ìý
This research work is concerned with the application of conceptual design of Unmanned Air Vehicle (UAV). UAV is used for surveillance and reconnaissance to serve for the defense as well as national security and intelligence purpose. Here NACA 0012 aerofoil profile is used to design UAV by using CFD (Computational Fluid Dynamics) software. The aim of this research is to investigate the flow patterns and determine the aerodynamic characteristics of NACA 0012 profile by varying the angle of attack and Reynolds Number numerically. The research is carried out with symmetric aerofoil with the chord length of 0.1m. The research work explained different aerodynamic characteristics like lift force and drag force, lift and drag coefficient, pressure distribution over aerofoil etc.
This document contains a lift calculation sheet for a crane job. It provides details of the crane configuration including crane type, boom length, jib type and length. It lists the weights of the crane, load, slings and other equipment. It calculates the total weight of the lift and confirms the lift is safe based on the crane's chart capacity at the actual pick radius.
A simplified nozzle ring CAD model was meshed and evaluated in ANSYS Mechanical to optimize the mesh for geometry and effectiveness. A representation of the European Transient Cycle was created to apply time-varied loads from Ricardo WAVE simulations. Four nozzle ring concepts were evaluated in ANSYS Mechanical to find equivalent stress and fatigue life, with all concepts showing stresses within the endurance limit of steel and practically infinite life with a good safety factor.
Thermo problems (cascade refrigeration cycle ) mohammad usman
Ìý
This document outlines a semester project for six students at Wah Engineering College, University of Wah. The project will cover topics including turbines, re-heaters, cascade refrigeration systems, and heat exchangers. It lists the group members and assumptions made. It also includes a sample problem solving a cascade refrigeration system, showing process points, temperatures, pressures, enthalpies and entropies. Questions are presented at the end for the students to answer as part of their project.
Analysis of wings using Airfoil NACA 4412 at different angle of attackIJMER
Ìý
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.
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil A...CrimsonPublishersRDMS
Ìý
Effect of Gap between Airfoil and Embedded Rotating Cylinder on the Airfoil Aerodynamic Performance by Najdat Nashat Abdulla* in Crimson Publishers: Peer Reviewed Material Science Journals
This document outlines the topics that will be covered in an aviation course, including electric aircraft systems, aircraft maintenance, batteries, aerodynamics, flight maneuvers, airspace, weather, maps, regulations, mission planning, safety management, and human factors. The course appears designed to teach students about remotely piloted aircraft systems. It will cover essential aeronautical knowledge on topics like flight principles, meteorology, navigation, and aviation rules and safety.
Jay Ryan R. Santos has experience designing various types of industrial structures including pipe racks, equipment structures, shelters, table tops, modular structures, vessel foundations, tank foundations, and mining equipment foundations. He has expertise in load calculations, steel and concrete design, lifting analysis, transportation analysis, and seismic analysis of industrial structures.
Turning Moment Diagram and Flywheel (TOM)Swagatika Pal
Ìý
This document discusses turning moment diagrams and flywheels. It explains that a turning moment diagram is a graphical representation of the torque on the crankshaft at different crank angles. It shows the torque is highest at 90 degrees and lowest at 0 and 180 degrees. The area under the curve represents the work done per revolution. A flywheel stores energy when torque is high and releases it when torque is low, reducing fluctuations in speed. The ratio of maximum speed variation to mean speed is called the coefficient of fluctuation of speed. A flywheel controls speed variations caused by uneven engine torque over each operating cycle.
Current Problem
No simple system exists to measure forces exerted on crane rails
Forces are currently only analyzed through theory
Very difficult to accurately predict lateral and vertical forces hence
support designs may be inadequate
A comparative flow analysis of naca 6409 and naca 4412 aerofoileSAT Publishing House
Ìý
This document analyzes and compares the flow properties of two airfoil profiles, the NACA 6409 and NACA 4412, using computational fluid dynamics (CFD) modeling in ANSYS. The analysis examines pressure distribution, lift and drag coefficients at varying angles of attack. The NACA 4412 was found to have better lift-to-drag ratio performance and is more efficient for practical applications compared to the NACA 6409.
IRJET-Subsonic Flow Study and Analysis on Rotating Cylinder AirfoilIRJET Journal
Ìý
This document presents a study on modifying the lift characteristics of a conventional symmetrical airfoil (NACA 0012) by adding a rotating cylinder. A numerical analysis and computational fluid dynamics simulation were conducted. Two cases were considered: a cylinder with 13mm diameter located at the 0.125 chord point, and a 15mm cylinder at the 0.25 chord point. The presence of a rotating cylinder was found to significantly increase the airfoil's lift at zero angle of attack through momentum injection, by up to 100%. It also delayed stall characteristics. The document outlines the methodology, including the airfoil geometry, range of air velocities and cylinder rotation speeds studied, and equations used to model static and total pressure.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
The document discusses modeling the behavior of thermoplastics in ANSYS. It describes the stress-strain behavior of thermoplastics under different loading conditions such as uniaxial tension, loading-unloading, creep, and relaxation. It also lists several material models in ANSYS that can be used to model different thermoplastic behaviors, such as elastic-plastic, hyperelastic, viscoelastic, and viscoplastic models. It provides guidance on choosing the appropriate material model based on the available experimental data, operating loading conditions, and simulation objectives.
This chapter discusses nonlinear materials and their behavior. It covers the basics of linear and nonlinear materials, elasticity, plasticity, hyperelasticity, and the models available in Workbench. It then provides two step-by-step examples: a Belleville washer made of steel and subjected to compression and release, and a rubber seal between two steel plates, with the top plate displaced downward. Force-displacement curves are generated for each example and residual stresses examined.
This document discusses the problem of thermal undershoot in transient thermal analysis and provides a solution. It shows a slab with uniform heat flux on one face and convection on the other, with the transient analysis resulting in temperatures falling below ambient. It then provides a relationship between element size and time step to avoid undershoot, and applies this to the model by increasing the number of elements from 30 to 10, resolving the undershoot issue.
This document describes a finite element analysis simulation of a riveting process in ANSYS and compares the results to experimental data. The simulation modeled a rivet being driven into a sheet metal joint. Material properties, boundary conditions, and a displacement-controlled loading process were defined. The results for bulge diameter and protruding rivet height matched well with experimental testing, with less than 2.13% difference. This validated the ability of the ANSYS simulation to accurately model the riveting process.
The document provides an overview of buckling analysis in ANSYS. It discusses buckling of columns with well-defined end conditions, buckling of a special column, and second order analysis of a simple beam. The preprocessing, solution, and postprocessing phases of ANSYS are outlined. Step-by-step instructions are given for modeling each example and obtaining the buckling load using eigenvalue buckling analysis. Manual calculations are also shown for comparison.
The document discusses the ANSYS Pressure Equipment Module which allows for modeling and analyzing pressure vessels and equipment. It provides an overview of the module's capabilities including parametric modeling of components, defining loads and boundary conditions, performing static and buckling analyses, and evaluating stress results. The document also provides examples of how to build geometry using the module's wizards to model different pressure equipment components and put them together into an assembly for analysis.
This document summarizes Katy Slater's experience and expertise in areas such as system integration, project management methodology, risk management, lessons learned, and emotional intelligence. It provides details on accelerated SAP implementations, product integrity management systems, finance architecture, and the importance of a single source of truth, change control, and dependencies in project management. It also outlines the project lifecycle including data analysis, testing, validation, and hypercare phases. Risks, issues, and lessons learned are discussed.
Presenter: Tom Marnik, Ansys
Validating your product design using simulation tools continues to grow in importance as well as complexity. Come share your ideas for the role that PLM can play in managing simulation data and supporting decision making based on results.
This document provides an overview of using ANSYS to analyze a bar in tension with a central hole. It describes the steps to:
1) Create the model geometry by defining element types, material properties, and generating the bar shape with a subtracted circle for the hole.
2) Mesh the geometry and apply boundary conditions and loads.
3) Solve the model and view displacement and stress results.
HPC Parallel Computing for FEA - Customer Examples (1 of 4)Ansys
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This presentation focuses on high-performance parallel computing for structural mechanics simulations! It is part of a series of 4 presentations in which - by means of real-world customer examples - we want to share with you some benefits of HPC and performance data as well as some background articles.
For convenience, we’ve split them up by major solution areas:
1: High-Performance Parallel Computing for FEA
2: High-Performance Parallel Computing for CFD
3: High-Performance Parametric Computing for FEA
4: High-Performance Parametric Computing for CFD
ANSYS SCADE Usage for Unmanned Aircraft VehiclesAnsys
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SCADE on-board the UAS P.1HH HammerHead
The Use of SCADE to develop the P.1HH Vehicle Control & Management System (Integrated Modular Avionics System) greatly reduced development time and effort.
Learn more about ANSYS SCADE Solutions for Aerospace & Defense http://bit.ly/1EdcsOJ
ANSYS Mechanical software provides a vast library of material models that can help users simulate various kinds of behaviors such as elasticity, plasticity, creep and hyperelasticity, just to name a few.
Although these models can be used to investigate the mechanical response of a large number of different materials such as metals, rubbers, biological tissues and special alloys, users may wish to incorporate their own material laws into ANSYS.
This task can be accomplished by means of a user-programmable feature named USERMAT, a subroutine that allows users to write their own material constitutive equations within a general material framework using ANSYS’ current element technology.
This presentation shows the use of USERMAT recently shown at the 2014 ANSYS Regional Conference in Eindhoven, The Netherlands.
Benefits of Intel Technologies for Engineering SimulationAnsys
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This presentation gives the perspective of an ISV (independent software vendor) on the usage of the latest Intel technologies for engineering simulation. It starts off with introducing ANSYS and why our customers have a continually increasing need for higher computing performance so that they can run faster, bigger, and more simulations. In order to meet this continually growing compute demand, it demonstrates how we have worked closely with Intel to optimize our software at different scales of parallelism (from workstation, server-based clusters to supercomputers). Key strategies to enable efficient parallel execution are discussed, and recent examples of the value of software optimization are shown.
Simulation-Based Engineering for Satellite ApplicationsAnsys
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The satellite industry is unforgiving. It is a definitive example of how right-first-time design is a must. Furthermore, customers are demanding heavier, more-sophisticated payloads be delivered to orbit at lower cost.
This document summarizes the design project of a connecting rod made from either stainless steel or aluminum alloy. It analyzes the materials' chemical compositions, stresses and strains, safety factors, weight and stiffness, and fatigue life. Stainless steel was found to have lower deformation, higher safety factor and stiffness, and a longer fatigue life than aluminum alloy, but aluminum alloy is lighter. Stainless steel is also cheaper. The conclusion is that stainless steel is a better material for the connecting rod based on its performance characteristics.
EXPERIMENTAL ANALYSIS OF THE WELD STRENGTH IN FRICTION STIR WELDING (FSW) OF ...IAEME Publication
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This research deals with the determination of the weld strength of the aluminum alloy of different grades in friction stir welding (FSW). The different grades of the plates are welded by the
different tool geometry namely as cylindrical tool and the tapered threaded tool. During the welding the rotational speed of tool and feed rate of the tool are kept constant. Testing of the specimens is carried out by ASME –SEC-IX and the weld strengths are compared.As a result it is found that the
threaded tool geometry gives the better weld strength and also the surface finish.
This document discusses how engineering simulation is becoming widespread in manufacturing industries. It notes that annual sales of CAE software have grown significantly in recent years and are projected to continue growing substantially. While most manufacturers now use simulation, the key to gaining competitive advantage is how companies apply simulation technology throughout their product development processes. Successful companies perform more upfront simulation to refine designs early instead refine problems late in development. This requires organizational changes to support broader and earlier use of simulation among engineers and designers. How companies commit to these changes will determine which gain the most business value from simulation-driven product development. The document contains several examples of companies using simulation in industries like yacht racing, composites, cosmetics, automotive, and power generation
Preface: The ReGenX Generator innovation operates with a US Patented Frequency Dependent Load Current Delay which delays the creation and storage of created Electromagnetic Field Energy around the exterior of the generator coil. The result is the created and Time Delayed Electromagnetic Field Energy performs any magnitude of Positive Electro-Mechanical Work at infinite efficiency on the generator's Rotating Magnetic Field, increasing its Kinetic Energy and increasing the Kinetic Energy of an EV or ICE Vehicle to any magnitude without requiring any Externally Supplied Input Energy. In Electricity Generation applications the ReGenX Generator innovation now allows all electricity to be generated at infinite efficiency requiring zero Input Energy, zero Input Energy Cost, while producing zero Greenhouse Gas Emissions, zero Air Pollution and zero Nuclear Waste during the Electricity Generation Phase. In Electric Motor operation the ReGen-X Quantum Motor now allows any magnitude of Work to be performed with zero Electric Input Energy.
Demonstration Protocol: The demonstration protocol involves three prototypes;
1. Protytpe #1, demonstrates the ReGenX Generator's Load Current Time Delay when compared to the instantaneous Load Current Sine Wave for a Conventional Generator Coil.
2. In the Conventional Faraday Generator operation the created Electromagnetic Field Energy performs Negative Work at infinite efficiency and it reduces the Kinetic Energy of the system.
3. The Magnitude of the Negative Work / System Kinetic Energy Reduction (in Joules) is equal to the Magnitude of the created Electromagnetic Field Energy (also in Joules).
4. When the Conventional Faraday Generator is placed On-Load, Negative Work is performed and the speed of the system decreases according to Lenz's Law of Induction.
5. In order to maintain the System Speed and the Electric Power magnitude to the Loads, additional Input Power must be supplied to the Prime Mover and additional Mechanical Input Power must be supplied to the Generator's Drive Shaft.
6. For example, if 100 Watts of Electric Power is delivered to the Load by the Faraday Generator, an additional >100 Watts of Mechanical Input Power must be supplied to the Generator's Drive Shaft by the Prime Mover.
7. If 1 MW of Electric Power is delivered to the Load by the Faraday Generator, an additional >1 MW Watts of Mechanical Input Power must be supplied to the Generator's Drive Shaft by the Prime Mover.
8. Generally speaking the ratio is 2 Watts of Mechanical Input Power to every 1 Watt of Electric Output Power generated.
9. The increase in Drive Shaft Mechanical Input Power is provided by the Prime Mover and the Input Energy Source which powers the Prime Mover.
10. In the Heins ReGenX Generator operation the created and Time Delayed Electromagnetic Field Energy performs Positive Work at infinite efficiency and it increases the Kinetic Energy of the system.
Air pollution is contamination of the indoor or outdoor environment by any ch...dhanashree78
Ìý
Air pollution is contamination of the indoor or outdoor environment by any chemical, physical or biological agent that modifies the natural characteristics of the atmosphere.
Household combustion devices, motor vehicles, industrial facilities and forest fires are common sources of air pollution. Pollutants of major public health concern include particulate matter, carbon monoxide, ozone, nitrogen dioxide and sulfur dioxide. Outdoor and indoor air pollution cause respiratory and other diseases and are important sources of morbidity and mortality.
WHO data show that almost all of the global population (99%) breathe air that exceeds WHO guideline limits and contains high levels of pollutants, with low- and middle-income countries suffering from the highest exposures.
Air quality is closely linked to the earth’s climate and ecosystems globally. Many of the drivers of air pollution (i.e. combustion of fossil fuels) are also sources of greenhouse gas emissions. Policies to reduce air pollution, therefore, offer a win-win strategy for both climate and health, lowering the burden of disease attributable to air pollution, as well as contributing to the near- and long-term mitigation of climate change.
The Golden Gate Bridge a structural marvel inspired by mother nature.pptxAkankshaRawat75
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The Golden Gate Bridge is a 6 lane suspension bridge spans the Golden Gate Strait, connecting the city of San Francisco to Marin County, California.
It provides a vital transportation link between the Pacific Ocean and the San Francisco Bay.
Lecture -3 Cold water supply system.pptxrabiaatif2
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The presentation on Cold Water Supply explored the fundamental principles of water distribution in buildings. It covered sources of cold water, including municipal supply, wells, and rainwater harvesting. Key components such as storage tanks, pipes, valves, and pumps were discussed for efficient water delivery. Various distribution systems, including direct and indirect supply methods, were analyzed for residential and commercial applications. The presentation emphasized water quality, pressure regulation, and contamination prevention. Common issues like pipe corrosion, leaks, and pressure drops were addressed along with maintenance strategies. Diagrams and case studies illustrated system layouts and best practices for optimal performance.
This PPT covers the index and engineering properties of soil. It includes details on index properties, along with their methods of determination. Various important terms related to soil behavior are explained in detail. The presentation also outlines the experimental procedures for determining soil properties such as water content, specific gravity, plastic limit, and liquid limit, along with the necessary calculations and graph plotting. Additionally, it provides insights to understand the importance of these properties in geotechnical engineering applications.