This document discusses mission adaptive compliant wings (MACW), which are wings that can adapt their shape to different flight conditions through morphing. MACW aim to fulfill conflicting mission requirements like high speed for fighters and high lift for bombers. This is achieved using compliant mechanisms, which distribute localized actuation through the elastic deformation of a monolithic structure without joints. Compliant wings can provide aerodynamic benefits like reduced drag and noise compared to conventional control surfaces.
The document discusses high-speed aerodynamics and several key concepts, including that compressibility effects become important at transonic and supersonic speeds. It describes research done on high-speed aircraft like the Bell X-1, which broke the sound barrier in 1947. The document also covers topics like the speed of sound, different flight regimes (subsonic, transonic, supersonic, hypersonic), and shock wave patterns that form at supersonic speeds.
The document discusses the concepts of stability, maneuverability, and controllability as they relate to aircraft design. It states that stability causes an aircraft to return to steady flight after a disturbance, maneuverability allows the pilot to move the aircraft easily about its axes, and controllability is the ability to respond to pilot inputs. However, increasing one of these characteristics typically decreases another, so aircraft designs involve compromises. The document then examines longitudinal, lateral, and directional stability in more detail.
The Directorate General of Civil Aviation (DGCA) is India's civil aviation regulatory body. This document outlines requirements and procedures for organizations involved in aircraft manufacturing, maintenance, testing, storage, and training. It discusses approval requirements for these organizations and categories they can seek approval in, such as manufacturer, maintenance, testing, fuel/lubricants, stores/distribution, and training. The document also provides detailed guidelines and safety procedures that must be followed for aircraft fueling operations.
Morphing Aircraft Technology – New Shapes for Aircraft Wing DesignMani5436
Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight.
Morphing poses several unique challenges when the wing loading is high. Very flexible materials are the designer’s first choice because they are easily reshaped.
he current use of multiple aerodynamic devices (such as flaps and slats) represents a simplification of the general idea behind morphing. Traditional control systems (with fixed geometry and/or location) give high aerodynamic performance over a fixed range and for a limited set of flight conditions.
1) When air flows around a corner at supersonic speeds, it does not create a shock wave but rather forms an expansion wave where the flow accelerates and Mach lines diverge.
2) In supersonic flow, expansion waves occur when the cross-sectional area of the flow path increases, lowering both temperature and pressure.
3) For a flat plate at a positive angle of attack in supersonic flow, the upper surface experiences an expansion wave at the leading edge and oblique shock at the trailing edge, producing uniform suction pressure to generate lift along with associated drag.
The document discusses high-speed aerodynamics and several key concepts, including that compressibility effects become important at transonic and supersonic speeds. It describes research done on high-speed aircraft like the Bell X-1, which broke the sound barrier in 1947. The document also covers topics like the speed of sound, different flight regimes (subsonic, transonic, supersonic, hypersonic), and shock wave patterns that form at supersonic speeds.
The document discusses the concepts of stability, maneuverability, and controllability as they relate to aircraft design. It states that stability causes an aircraft to return to steady flight after a disturbance, maneuverability allows the pilot to move the aircraft easily about its axes, and controllability is the ability to respond to pilot inputs. However, increasing one of these characteristics typically decreases another, so aircraft designs involve compromises. The document then examines longitudinal, lateral, and directional stability in more detail.
The Directorate General of Civil Aviation (DGCA) is India's civil aviation regulatory body. This document outlines requirements and procedures for organizations involved in aircraft manufacturing, maintenance, testing, storage, and training. It discusses approval requirements for these organizations and categories they can seek approval in, such as manufacturer, maintenance, testing, fuel/lubricants, stores/distribution, and training. The document also provides detailed guidelines and safety procedures that must be followed for aircraft fueling operations.
Morphing Aircraft Technology – New Shapes for Aircraft Wing DesignMani5436
Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight.
Morphing poses several unique challenges when the wing loading is high. Very flexible materials are the designer’s first choice because they are easily reshaped.
he current use of multiple aerodynamic devices (such as flaps and slats) represents a simplification of the general idea behind morphing. Traditional control systems (with fixed geometry and/or location) give high aerodynamic performance over a fixed range and for a limited set of flight conditions.
1) When air flows around a corner at supersonic speeds, it does not create a shock wave but rather forms an expansion wave where the flow accelerates and Mach lines diverge.
2) In supersonic flow, expansion waves occur when the cross-sectional area of the flow path increases, lowering both temperature and pressure.
3) For a flat plate at a positive angle of attack in supersonic flow, the upper surface experiences an expansion wave at the leading edge and oblique shock at the trailing edge, producing uniform suction pressure to generate lift along with associated drag.
This document discusses aircraft structural design limits and flight envelopes. It explains that flight envelopes graphically show the speed and load factor limits an aircraft can withstand based on factors like stall speed and maneuvering capabilities. The curves account for factors like altitude and critical Mach number. Load factors in the flight envelope are determined based on expected maneuvering loads and gust loads, with statistical analysis used to estimate extreme loads the aircraft may encounter over its operational life. Structural design limits like limit load, proof load, and ultimate load are set to ensure the aircraft can withstand expected loads with safety margins.
This document provides a structural outline of the EASA Airworthiness Regulations. It is a Publication of Wing Engineering Limited's Key Points Resource Library.
This document outlines the course objectives and content for Aerodynamics 301A taught at Cairo University's Faculty of Engineering. The course aims to teach students: 1) how to predict aerodynamic forces on aircraft components and whole aircraft; 2) how to determine air properties moving internally through engines; and 3) how to apply various aerodynamic principles to different applications. The course covers topics such as the governing equations of fluid motion, potential flow theory, and finite wing theory.
This document provides an overview of the autopilot and flight management systems on an aircraft. It describes the key components like the flight management and guidance system (FMGS), flight management and guidance computers (FMGCs), flight control unit (FCU), and autopilot. It explains how the autopilot, flight directors, and auto thrust systems work together to control the aircraft and achieve different flight modes. The flight mode annunciations (FMAs) indicate the engaged, armed and status of the auto flight systems.
Angle of attack | Flight Mechanics | GATE AerospaceAge of Aerospace
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 outlines the aircraft design process from initial requirements definition through detailed design, testing, and certification. It discusses establishing basic and general requirements, conducting feasibility studies, specifying detailed requirements, conceptual and preliminary design phases involving configuration selection, performance modeling, and optimization. Later phases include detailed design, ground and flight testing, and certification to clear the aircraft for intended operations. The process is iterative with frequent trade-offs and refinement of requirements and design.
Wind tunnels come in several types depending on their design and airflow characteristics. The document describes blow down, atmospheric entry, high enthalpy, and continuous flow wind tunnels. Continuous flow wind tunnels can be open circuit for subsonic or supersonic testing, or closed circuit. Open circuit tunnels work by drawing in air and exhausting it, while closed circuit wind tunnels recirculate the air through a compressor. The different wind tunnel types are used to simulate various flow conditions for testing aircraft and missile components.
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
This chapter discusses the key components of aircraft structures including the fuselage, wings, and stabilizing surfaces. It covers the different types of loads aircraft structures must withstand such as tension, compression, bending, and torsion. The chapter also examines various construction methods for fuselages including monocoque, semi-monocoque, and framework designs. Common materials used in aircraft structures like aluminum alloys and composites are also discussed.
This presentation discusses swept wing configurations and their applications for supersonic flight. Swept wings reduce wave drag at transonic speeds by angling shock waves away from the aircraft. Swept wings were first developed in Germany in the 1930s and became prominent with aircraft like the MiG-15 and F-86. Variations include forward swept wings, which provide maneuverability but are expensive, and variable sweep wings which can change sweep angle during flight. Swept wings provide benefits like lateral stability and delaying compressibility effects at transonic speeds.
This document discusses aircraft take-off and landing performance. It provides equations to calculate take-off ground roll distance and total take-off distance based on factors like thrust, weight, wing area, and lift coefficient. The document also discusses regulations for landing performance and provides an empirical equation to calculate total landing distance. It concludes by providing recommended lift coefficient ranges for take-off and landing for fighter and transport aircraft design.
This document provides an overview of aircraft wings, including their:
- Historical development from ancient kites to the Wright brothers' fixed-wing aircraft.
- Construction, with internal structures like ribs, spars, stringers, and skin covering the framework. Wings also contain fuel tanks, flaps, and other devices.
- Functions, as wings generate lift through Bernoulli's principle and critical angle of attack. Wing design factors like aspect ratio and camber also affect lift.
- Types based on position (fixed or movable) and structure (cantilever or strut-braced). Stability devices like ailerons and flaps are also described.
- Unconventional designs that
This document provides an overview of aeroelasticity, including its history, classifications, and precautions. It discusses how aeroelasticity studies the interaction between inertial, structural and aerodynamic forces. The document outlines the necessity of studying aeroelasticity effects for rotor design, wind energy, and to understand catastrophic failures. It then describes different types of static and dynamic aeroelasticity like divergence, control reversal, flutter, buffeting, and transonic phenomena. Precautions like testing and analysis are discussed.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What Is Blended Wing Body, History of BWB, How Airplanes Fly, Aircraft Control Surfaces, Design and Structure of BWB, Advantages and Disadvantages, Conventional aircraft vs. BWB, Future Scope and Challenges
- Airport firefighters must thoroughly familiarize themselves with the airport layout and surroundings in order to safely and efficiently perform their jobs. This includes understanding the airport type, classification, runway and taxiway systems, signs, and other key areas.
- Familiarity with these airport features can save valuable time during an emergency response and help protect both crash victims and the responders themselves. The design and infrastructure of the airport can significantly impact firefighting operations.
The document discusses aircraft performance certification and optimizing an aircraft's payload and range ability given physical and environmental limitations. It covers manufacturer's weight empty, operating empty weight, maximum zero fuel weight, maximum takeoff weight, and how payload and fuel affect an aircraft's range. Changing design aspects like maximum takeoff weight, zero fuel weight, and fuel capacity can impact the payload-range envelope.
Morphing of Aircraft Wings
This document discusses morphing technology for aircraft wings. Morphing allows wings to change shape to better match flight conditions. It can improve performance, efficiency, and adaptability. Wing morphing technologies include folding, sweeping, extending wings, and changing camber. This allows control of wing area, aspect ratio, and sweep angle. Shape memory alloys are used for actuation components. Advantages of morphing wings include improved performance, control, stealth, reduced drag and weight. Challenges remain in developing morphing wing technologies that can withstand flight conditions.
The document discusses several technologies related to adaptive and fluidic flight control systems:
- Fluidics uses fluids rather than electronics for control operations, with applications in aircraft circulation control and thrust vectoring for benefits like lower mass and complexity.
- The Boeing X-53 Active Aeroelastic Wing program tested controlling wing twist using multiple leading and trailing edge controls on a modified F/A-18 to provide improved wing control and efficiency.
- Adaptive compliant wings can flexibly change aspects of their shape in flight using mechanisms like variable-camber trailing edges or twist, as demonstrated on a section tested on the White Knight aircraft.
This document discusses aircraft structural design limits and flight envelopes. It explains that flight envelopes graphically show the speed and load factor limits an aircraft can withstand based on factors like stall speed and maneuvering capabilities. The curves account for factors like altitude and critical Mach number. Load factors in the flight envelope are determined based on expected maneuvering loads and gust loads, with statistical analysis used to estimate extreme loads the aircraft may encounter over its operational life. Structural design limits like limit load, proof load, and ultimate load are set to ensure the aircraft can withstand expected loads with safety margins.
This document provides a structural outline of the EASA Airworthiness Regulations. It is a Publication of Wing Engineering Limited's Key Points Resource Library.
This document outlines the course objectives and content for Aerodynamics 301A taught at Cairo University's Faculty of Engineering. The course aims to teach students: 1) how to predict aerodynamic forces on aircraft components and whole aircraft; 2) how to determine air properties moving internally through engines; and 3) how to apply various aerodynamic principles to different applications. The course covers topics such as the governing equations of fluid motion, potential flow theory, and finite wing theory.
This document provides an overview of the autopilot and flight management systems on an aircraft. It describes the key components like the flight management and guidance system (FMGS), flight management and guidance computers (FMGCs), flight control unit (FCU), and autopilot. It explains how the autopilot, flight directors, and auto thrust systems work together to control the aircraft and achieve different flight modes. The flight mode annunciations (FMAs) indicate the engaged, armed and status of the auto flight systems.
Angle of attack | Flight Mechanics | GATE AerospaceAge of Aerospace
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 outlines the aircraft design process from initial requirements definition through detailed design, testing, and certification. It discusses establishing basic and general requirements, conducting feasibility studies, specifying detailed requirements, conceptual and preliminary design phases involving configuration selection, performance modeling, and optimization. Later phases include detailed design, ground and flight testing, and certification to clear the aircraft for intended operations. The process is iterative with frequent trade-offs and refinement of requirements and design.
Wind tunnels come in several types depending on their design and airflow characteristics. The document describes blow down, atmospheric entry, high enthalpy, and continuous flow wind tunnels. Continuous flow wind tunnels can be open circuit for subsonic or supersonic testing, or closed circuit. Open circuit tunnels work by drawing in air and exhausting it, while closed circuit wind tunnels recirculate the air through a compressor. The different wind tunnel types are used to simulate various flow conditions for testing aircraft and missile components.
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
This chapter discusses the key components of aircraft structures including the fuselage, wings, and stabilizing surfaces. It covers the different types of loads aircraft structures must withstand such as tension, compression, bending, and torsion. The chapter also examines various construction methods for fuselages including monocoque, semi-monocoque, and framework designs. Common materials used in aircraft structures like aluminum alloys and composites are also discussed.
This presentation discusses swept wing configurations and their applications for supersonic flight. Swept wings reduce wave drag at transonic speeds by angling shock waves away from the aircraft. Swept wings were first developed in Germany in the 1930s and became prominent with aircraft like the MiG-15 and F-86. Variations include forward swept wings, which provide maneuverability but are expensive, and variable sweep wings which can change sweep angle during flight. Swept wings provide benefits like lateral stability and delaying compressibility effects at transonic speeds.
This document discusses aircraft take-off and landing performance. It provides equations to calculate take-off ground roll distance and total take-off distance based on factors like thrust, weight, wing area, and lift coefficient. The document also discusses regulations for landing performance and provides an empirical equation to calculate total landing distance. It concludes by providing recommended lift coefficient ranges for take-off and landing for fighter and transport aircraft design.
This document provides an overview of aircraft wings, including their:
- Historical development from ancient kites to the Wright brothers' fixed-wing aircraft.
- Construction, with internal structures like ribs, spars, stringers, and skin covering the framework. Wings also contain fuel tanks, flaps, and other devices.
- Functions, as wings generate lift through Bernoulli's principle and critical angle of attack. Wing design factors like aspect ratio and camber also affect lift.
- Types based on position (fixed or movable) and structure (cantilever or strut-braced). Stability devices like ailerons and flaps are also described.
- Unconventional designs that
This document provides an overview of aeroelasticity, including its history, classifications, and precautions. It discusses how aeroelasticity studies the interaction between inertial, structural and aerodynamic forces. The document outlines the necessity of studying aeroelasticity effects for rotor design, wind energy, and to understand catastrophic failures. It then describes different types of static and dynamic aeroelasticity like divergence, control reversal, flutter, buffeting, and transonic phenomena. Precautions like testing and analysis are discussed.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What Is Blended Wing Body, History of BWB, How Airplanes Fly, Aircraft Control Surfaces, Design and Structure of BWB, Advantages and Disadvantages, Conventional aircraft vs. BWB, Future Scope and Challenges
- Airport firefighters must thoroughly familiarize themselves with the airport layout and surroundings in order to safely and efficiently perform their jobs. This includes understanding the airport type, classification, runway and taxiway systems, signs, and other key areas.
- Familiarity with these airport features can save valuable time during an emergency response and help protect both crash victims and the responders themselves. The design and infrastructure of the airport can significantly impact firefighting operations.
The document discusses aircraft performance certification and optimizing an aircraft's payload and range ability given physical and environmental limitations. It covers manufacturer's weight empty, operating empty weight, maximum zero fuel weight, maximum takeoff weight, and how payload and fuel affect an aircraft's range. Changing design aspects like maximum takeoff weight, zero fuel weight, and fuel capacity can impact the payload-range envelope.
Morphing of Aircraft Wings
This document discusses morphing technology for aircraft wings. Morphing allows wings to change shape to better match flight conditions. It can improve performance, efficiency, and adaptability. Wing morphing technologies include folding, sweeping, extending wings, and changing camber. This allows control of wing area, aspect ratio, and sweep angle. Shape memory alloys are used for actuation components. Advantages of morphing wings include improved performance, control, stealth, reduced drag and weight. Challenges remain in developing morphing wing technologies that can withstand flight conditions.
The document discusses several technologies related to adaptive and fluidic flight control systems:
- Fluidics uses fluids rather than electronics for control operations, with applications in aircraft circulation control and thrust vectoring for benefits like lower mass and complexity.
- The Boeing X-53 Active Aeroelastic Wing program tested controlling wing twist using multiple leading and trailing edge controls on a modified F/A-18 to provide improved wing control and efficiency.
- Adaptive compliant wings can flexibly change aspects of their shape in flight using mechanisms like variable-camber trailing edges or twist, as demonstrated on a section tested on the White Knight aircraft.
The document summarizes research on developing biologically-inspired unconventional control surfaces for aircraft. A hobby aircraft was modified with a morphing inner wing using shape memory alloy actuators to allow continuous camber change, inspired by bird wings. An outer wing section was made sweep-adjustable using overlapping feather surfaces to provide yaw control. A gimbaled tail without vertical stabilizer provided pitch and rotation like bird tails but resulted in excessive instability. Further research is needed to optimize performance gains from these biologically-inspired designs.
1. The oscillating wind energy harvester was designed to harness energy from lower wind speeds of 5-8 m/s through vortex shedding from its oscillating wings.
2. It utilizes a gear and linkage system to efficiently transmit power from the oscillating wings to a generator. Extensive modeling and testing was done to optimize the design.
3. The device was manufactured using aluminum, steel, composites and other materials. CNC machining, laser cutting and resin infusion were used to fabricate parts to tight tolerances to achieve the desired kinematics and performance.
The document discusses the aerospike engine, which maintains aerodynamic efficiency across altitudes unlike conventional bell nozzles. It works by directing exhaust radially inward toward the nozzle axis, compensating for changes in ambient pressure. Aerospike engines offer benefits like reduced size and fuel consumption compared to bell engines. Recent organizations have been developing aerospike technology further for applications like small satellite launch vehicles.
Propulsion Selection and Analysis for Unmanned Aerial Vehicles for SAE Aero D...theijes
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.
1) A prototype twisting wing was developed using shape memory alloy actuators to enable variable wing twist.
2) Benchtop and wind tunnel testing showed that the wing could be twisted up to 10 degrees using a PID controller to precisely control wing twist.
3) Wind tunnel tests measured how lift and drag coefficients varied with angle of attack for different levels of controlled wing twist.
A Brief Study, Research, Design, Analysis on Multi Section Variable Camber WingIJERA Editor
Minimizing fuel consumption is one of the major concerns in the aviation industry. In the past decade, there
have been many attempts to improve the fuel efficiency of aircraft. One of the methods proposed is to vary the
lift-to-drag ratio of the aircraft in different flight conditions. To achieve this, the wing of the airplane must be
able to change its configuration during flight, corresponding to different flight regimes.In the research presented
in this thesis, the aerodynamic characteristics of a multisection, variable camber wing were investigated. The
model used in this research had a 160mm chord and a 200mm wingspan, with the ribs divided into 4 sections.
Each section was able to rotate approximately 5 degrees without causing significant discontinuity on the wing
surface. Two pneumatic actuators located at the main spar were used to morph the wing through mechanical
linkages. The multi-section variable camber wing model could provide up to 10 percent change in camber from
the baseline configuration, which had a NACA0015 section.The wing was tested in the free-jet wind tunnel at
three different Reynolds numbers: 322000, 48000, and 636000. Static tests were performed to obtain lift and
drag data for different configurations. Two rigid wings in baseline and camber configuration were built and
tested to compare the test data with variable camber wing. The wind tunnel test results indicated that the multisection
variable camber wing provided a higher lift than the rigid wing in both configurations whereas high drag
was also generated on the variable camber wing due to friction drag on the wing skin. The larger drag value
appeared on variable camber wing in baseline configuration than in cambered configuration resulting in lower
lift-to-drag ratio as compared to the baseline rigid wing whereas the variable camber wing in cambered
configuration had higher lift-to-drag ratio than the cambered rigid wing.
This document summarizes a student project to design and test an aeroelastic composite wing that can passively deform through bend-twist coupling to produce downforce like an active aerodynamic wing. The students fabricated composite wings with various fiber orientations and tested them in a wind tunnel to measure lift, drag, and deformation. Preliminary results showed the wings achieving bend-twist coupling but fluttering unpredictably at high wind speeds, preventing conclusions about downforce performance compared to a rigid wing.
he presence of civil aviation has affected our economic way of
life, it has made changes in our social and cultural viewpoints, and
has had a hand in shaping the course of political history.
The sociological changes brought about by air transportation are
perhaps as important as those it has brought about in the economy.
People have been brought closer together and so have reached a better understanding of interregional problems. Industry has found new
ways to do business. The opportunity for more frequent exchanges of
information has been facilitated, and air transport is enabling more
people to enjoy the cultures and traditions of distant lands.
In recent years, profound changes in technology and policy have
had significant impacts on civil aviation and its supporting airport
infrastructure. The industry continues to grow in numbers of aircraft,
passengers and cargo carried, and markets served, from nonstop
service on superjumbo aircraft between cities half-way across the
planet, to privately operated “very light jets” between any of thousands of small airports domestically. Growth encouraged from technological advancements countered with increased constraints on the
civil aviation system due to increased capacity limitations, security
regulations, and financial constraints have resulted in ever increasing
challenges to airport planning and design.
Civil aviation is typically considered in three sectors, commercial
service aviation (more commonly known as air carriers or airlines), air
cargo, and general aviation. Although the lines between these traditional sectors are becoming increasingly blurred, the regulations
and characteristics regarding their individual operations are often
mutually exclusive, and as such, those involved in airport planning
and design should have an understanding of each sector
A Study of Wind Turbine Blade Power Enhancement Using Aerodynamic Properties IJMER
Technological advancements have improvised them over time. In this paper we shall glance at
the features. Wind energy is the most popular renewable energy. In order to increase the use of wind
energy, it is important to develop wind turbine rotor models with high rotation rates and power
coefficients. These elemental forces are summed along the span of the blade to calculate the total forces
and moments exerted on the turbine. This study aimed at manufacturing highly efficient wind turbine
rotor models using NACA profiles.
This document provides an overview of air caster transportation systems produced by Aerofilm Systems. It describes various air caster products such as permanently installed air caster systems, modular air caster systems, air casters, lift cushions, and custom engineered solutions. The main benefits of air caster transportation systems are listed as being ergonomic, causing no floor damage, suitable for heavy loads, friction-free movement, low maintenance, and accurate positioning.
This document provides an overview of air caster transportation systems produced by Aerofilm Systems. It describes various air caster products such as permanently installed air caster systems, modular air caster systems, air casters, lift cushions, and custom engineered solutions. The main benefits of air caster transportation systems are listed as being ergonomic with low effort required, suitable for heavy loads, friction-free movement, accurate positioning, and applicable in cleanroom environments.
This document provides an overview of air caster transportation systems produced by Aerofilm Systems. It describes various air caster products such as permanently installed air caster systems, modular air caster systems, air casters, lift cushions, and custom engineered solutions. The main benefits of air caster transportation systems are listed as being ergonomic, causing no floor damage, suitable for heavy loads, friction-free movement, low maintenance, and accurate positioning.
Computational Investigation on the Effect of Fences on Aerodynamic Characteri...ijtsrd
A computational study, to improve the stall characteristics of wing at high angles of attack, with and without fence configuration is done here. Wing fences, also known as boundary layer fences and potential fences are fixed aerodynamic devices attached to aircraft in the exactly middle of the span and two fences are fixed in the exactly middle of the wing span and two fences are fixed at 25 percentage of wing span from their corresponding wing tip. The main aim of this research is to improve the lift and stalling angle. A rectangular wing with different angles of attack is used. Modeling was done in CATIA V5 R20 and meshing and analyzing was taken in ANSYS workbench and CFX. Then the graph is drawn for CL and CD for various angles of attack and various models. Mohamed Hamdan. A "Computational Investigation on the Effect of Fences on Aerodynamic Characteristics of an Aircraft Wing" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-5 | Issue-4 , June 2021, URL: https://www.ijtsrd.compapers/ijtsrd43687.pdf Paper URL: https://www.ijtsrd.comengineering/aeronautical-engineering/43687/computational-investigation-on-the-effect-of-fences-on-aerodynamic-characteristics-of-an-aircraft-wing/mohamed-hamdan-a
This document summarizes Rishabh Verma's graduate final project involving the modeling and analysis of a multi-element rear wing for a race car using CAD/CAM software. The project objectives are to model various wing profiles with and without a Gurney flap in SolidWorks and analyze the downforce, drag, and angle of attack using OpenFOAM computational fluid dynamics software. The document provides background on airfoil theory, descriptions of the modeling and analysis software used, sample airfoil coordinate data and wing profiles, and preliminary results analyzing drag force, lift force, and lift-to-drag ratio at different angles of attack.
The document summarizes research on morphing airfoil and wing technologies being conducted by Dr. Benjamin Woods and his team. It describes the FishBAC (Fish Bone Active Camber) airfoil which uses a compliant core and skin to enable changes in camber, resulting in up to 25% increase in lift to drag ratio. It also presents the Adaptive Aspect Ratio wing concept that allows the span to increase by 100% using a telescoping spar, sliding ribs, and an elastomeric skin driven by a strap. Wind tunnel tests and analysis show the technologies are effective. The research aims to further explore applications in aircraft, wind turbines, and more through collaboration.
The document presents a presentation on the aerodynamic and structural analysis of winglets using composite materials. It was presented by three students for their Bachelor of Technology degree in Aeronautical Engineering. The presentation introduces winglets, describes how they work to reduce drag, and analyzes lifting and drag forces with and without winglets using computational fluid dynamics. Key results showed an increase in lift and decrease in drag when winglets were added, improving aerodynamic efficiency.
This document discusses a study that explored trade-offs in using low-lift versus high-lift airfoils for the tip region of stall-regulated horizontal axis wind turbines (HAWTs). A blade design optimization method was used to identify the practical lower limit of maximum lift coefficients for tip airfoils between 0.7-1.2. Blades were optimized for both maximum annual energy production and minimum cost of energy. The results indicate that reducing the maximum lift coefficient below upper limits considered increases cost of energy, suggesting higher lift coefficient tip airfoils are preferable as turbine size increases if they have gentle stall characteristics.
Thinking of getting a dog? Be aware that breeds like Pit Bulls, Rottweilers, and German Shepherds can be loyal and dangerous. Proper training and socialization are crucial to preventing aggressive behaviors. Ensure safety by understanding their needs and always supervising interactions. Stay safe, and enjoy your furry friends!
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How to Manage Your Lost Opportunities in Odoo 17 CRMCeline George
Odoo 17 CRM allows us to track why we lose sales opportunities with "Lost Reasons." This helps analyze our sales process and identify areas for improvement. Here's how to configure lost reasons in Odoo 17 CRM
How to Fix the Import Error in the Odoo 17Celine George
An import error occurs when a program fails to import a module or library, disrupting its execution. In languages like Python, this issue arises when the specified module cannot be found or accessed, hindering the program's functionality. Resolving import errors is crucial for maintaining smooth software operation and uninterrupted development processes.
A review of the growth of the Israel Genealogy Research Association Database Collection for the last 12 months. Our collection is now passed the 3 million mark and still growing. See which archives have contributed the most. See the different types of records we have, and which years have had records added. You can also see what we have for the future.
Macroeconomics- Movie Location
This will be used as part of your Personal Professional Portfolio once graded.
Objective:
Prepare a presentation or a paper using research, basic comparative analysis, data organization and application of economic information. You will make an informed assessment of an economic climate outside of the United States to accomplish an entertainment industry objective.
Main Java[All of the Base Concepts}.docxadhitya5119
This is part 1 of my Java Learning Journey. This Contains Custom methods, classes, constructors, packages, multithreading , try- catch block, finally block and more.
Assessment and Planning in Educational technology.pptxKavitha Krishnan
In an education system, it is understood that assessment is only for the students, but on the other hand, the Assessment of teachers is also an important aspect of the education system that ensures teachers are providing high-quality instruction to students. The assessment process can be used to provide feedback and support for professional development, to inform decisions about teacher retention or promotion, or to evaluate teacher effectiveness for accountability purposes.
it describes the bony anatomy including the femoral head , acetabulum, labrum . also discusses the capsule , ligaments . muscle that act on the hip joint and the range of motion are outlined. factors affecting hip joint stability and weight transmission through the joint are summarized.
This slide is special for master students (MIBS & MIFB) in UUM. Also useful for readers who are interested in the topic of contemporary Islamic banking.
Exploiting Artificial Intelligence for Empowering Researchers and Faculty, In...Dr. Vinod Kumar Kanvaria
Exploiting Artificial Intelligence for Empowering Researchers and Faculty,
International FDP on Fundamentals of Research in Social Sciences
at Integral University, Lucknow, 06.06.2024
By Dr. Vinod Kumar Kanvaria
A workshop hosted by the South African Journal of Science aimed at postgraduate students and early career researchers with little or no experience in writing and publishing journal articles.
This presentation was provided by Steph Pollock of The American Psychological Association’s Journals Program, and Damita Snow, of The American Society of Civil Engineers (ASCE), for the initial session of NISO's 2024 Training Series "DEIA in the Scholarly Landscape." Session One: 'Setting Expectations: a DEIA Primer,' was held June 6, 2024.
5. INTRODUCTION
Improving aircrafts efficiency is one of
the key element of Aeronautics.
For increasing aircraft efficiency, 50%
of the researches are aimed
To reduce drag.
To increase lift.
To reduce structural weight.
To reduce system power take up.
7. DRAG AND LIFT
(a) Drag reduction is achieved by
Reducing surface friction drag.
Reducing form drag.
Reducing induced drag.
(b) Lift increase is achieved by
Finding the most efficient Angle of
Attack.
Inventing new lift augmenting
devices.
Changing wing shape and size.
8. NEW TRENDS IN
AERODYNAMICS
Blended wing body or BWB.
Twisteron.
Fanwing.
Spiroid Winglets.
Mission adaptive compliant
wings.
14. MISSION ADAPTIVE
WINGS
The mission adaptive wings are the
wings which should be able to
adapt itself to different flying
conditions and should be able to
fulfil conflicting mission
requirements by morphing their
wings.
15. CONFLICTING MISSION REQUIREMENTS
We want our aircraft to be used as
fighter i.e for high speed as well as
bomber i.e for high lift.
FIGHTER BOMBER
16. CONFLICTING MISSION REQUIREMENTS
We want our aircrafts to cruise at relatively
high speeds and at the same time it should
be, easily or efficiently, able to support lower
speeds such as those required for loitering,
taking off, or landing.
17. MORPHING
Morphing can be defined as “to cause
something to change its outward
Appearance”.
Wing that can sense its environment
and adapt its shape to perform
optimally in a wide range of flight
conditions.
25. MORPHING REQUIREMENTS
Morphing requirements are:-
Actuation system-
Change in the airfoil shape in a controlled manner
by different methods.
Wing structural characteristics-
withstand the aerodynamic forces and wing
loadings.
Must be able to achieve a seamless morph
Compromise between stiffness and flexibility in the
selected materials.
Aerodynamic characteristics -
Must ensure that the change in shape will result in
measurable changes in flight characteristics.
26. MORPHING METHODS
MULTIPLE ACTUATORS.
•To control the camber of the
aerofoil multiple actuators
distributed throughout the
wings were used.
•Fibre glass flexi panels were
bent by conventional rigid
link mechanism.
•These are aerodynamically
superior than conventional
flaps as their were no
discontinuities and seams.
27. INCHWORM ACTUATORS
Wing camber can be varied by employing
inchworm actuators arranged in a truss manner
within the wing ribs.
29. INTELLIGENT
ACTUATORS
PIEZOELECTRIC MATERIALS. Relation
between mechanical stress and an electrical
voltage. Its reversible process.
Disadvantages. Inadequate
displacement. Require excessive power, and/or
are complex and heavy.
30. Shape Memory Alloy. Shape memory alloys
(SMAs) are metals that "remember" their original
shapes. SMAs actuators are materials that "change
shape and mechanical characteristics in response to
temperature or electromagnetic fields.
Disadvantages. Insufficient Bandwidth. Require
excessive power, and/or are complex and heavy.
32. The energy was drawn from a few remotely
located actuators and then this energy was
distributed to the structure through some
intermediary mechanism.
Methodology employed is distributed
compliance rather than distributed actuation
Compliant Mechanisms (Structures) are
structures that are specifically optimized to
distribute localized actuation (strain) to
change the shape of the structure.
34. COMPLIANT MECHANISMS
•Monolithic.
•Joint Less Structures
•These structures exploits elasticity of the
material to produce desired functionalities.
•These functionalities can include force or motion
transmission, motion guidance, shape morphing
and energy storage and release.
35. COMPLIANT MECHANISM
The arrangement of the material within the
compliant mechanism is optimized so
compliance is distributed through small strains
to produce large deformations.
36. COMPLIANT MECHANISM
Note that the design does not embody any
flexural joints, which create stress concentrations
and poor fatigue life.
Compliant structure deforms as a whole and
avoids high-stress concentrations in which the
flexion is concentrated in localized regions.
38. COMPLIANT MECHANISM
These are flexible mechanisms that
transfer an input force
or displacement to another point
through elastic body deformation. These
are usually monolithic (single-piece) or
joint less structure.
39. ADVANTAGES
Minimize or eliminate assembly requirements.
Excellent repeatability since there is no
backlash.
No joints mean no joint friction, backlash, or
need for lubrication.
Can easily couple with modern actuators.
Can create motions not possible with
conventional rigid devices.
Materials friendly.
Weight reduction.
Fatigue resistant.
40. COMPLIANT MECHANISM
WINGS
When normal aerofoils or wings are made
mission adaptive by using the new technology
called compliant mechanism then they are
termed as mission adaptive compliant wings.
The MACW technology provides lightweight,
low-power, variable geometry re-shaping of the
upper and lower surface with no seams or
discontinuities.
42. MAKING OF MAW BY
COMPLIANT MECHANISM
FlexSys Inc, has developed a unique, variable-geometry,
trailing edge flap that can re-contour
the airfoil upper and lower surface.
43. Combined compliant flap system to a Natural
Laminar Flow (NLF) airfoil.
This airfoil can theoretically achieve up to 65%
chord laminar flow on the upper surface and up
to 90% chord laminar flow on the lower surface
as opposed to a conventional hinged flap which
can introduce flow separation at the flap knee.
44. The airfoil flap system is optimized to maximize
the laminar boundary layer extent over a broad
lift coefficient range.
Data from flight testing revealed laminar flow
was maintained over approximately 60% of the
airfoil chord for much of the lift range.
Drag results revealed that that was considerable
decrease in drag and hence good lift/ drag ratio.
FlexSys has developed morphing surfaces for
both the leading and trailing edge.
50. NOISE REDUCTION
Compliant structures enable development of a
seamless transition between the fixed and flapped
portions of the wing as shown in Figure.
51. • The main purpose of this region is to reduce
noise associated with the turbulent airflow
generated by the discontinuous surfaces at the
flap ends when the high lift flaps are deployed
for landing.
MAW FLAP CONVENTIONAL FLAP
52. MACW flaps can require less force and power
than a comparably sized conventional flap.
The MACW flap required 33% less actuation
force. This is because a compliant flap with 33%
shorter chord than a conventional flap can
provide the same CL and Cm performance.
54. ADDITIONAL BENEFITS
Can move into complex predetermined positions
with minimal force.
Can be locked in place at any desired
configuration.
Just as stiff and strong as a conventional control
surface.
The elimination of discontinuities in the flap
surface can provide lower drag and higher
control authority than comparable hinged flaps.
The elimination of joints and seams make the
flap more impervious to icing and fouling from
debris.
55. CONCLUSION
Sooner or later it will be possible to
make wings without ailerons, flaps
and thousands of individual parts.
They will have in principle only one
component, which continually
changes shape.
Do you find any similarities between these photograph? Yes, the similarity is that the both of them are changing the shape and size of there wings. But the question is why they are doing so? The answer is that they are trying to adopt themselves according to different flying condition.
This type of wings are called mission adaptive wings and technology by which we will achieve this change is called compliant technology . Hence the wings which changes its shape and size according to the mission by using compliant technology is called mission adaptive compliant wings. Mission adaptive compliant wing improves the efficiency of the aircraft. How its improve the efficiency of the aircraft? What are the other methods to improve efficiency. Let’s see.
Aircrafts efficiency can be increased by these methods. 50% of the researches to increase the aircraft efficiency are aimed to reduce drag, To increase lift To reduce structural weight To reduce system power take up. Look at these points carefully you will find that these are the four forces which balance the aircraft in the air.
Balancing these four forces in a most efficient way has been the biggest challenge for Aerodynamic since its invention . As Managing the weight and thrust are structural and propulsion problems, we will look into lift and drag which are more or less aerodynamics problem
By manipulating these forces we can use them to our advantage. To achieve this, the aero dynamists keep testing new designs. Lets have a look to some the latest trends to increase the efficiency of the aircraft by manipulating these two forces.
These are some latest trends which increases the aircraft efficiency by reducing drag and increasing lift and good lift by drag ratio.
Improved fuel economy due to less drag.
Increase lift to drag ratio by an amazing 50%.
Weight reduced by 25%.
Reduced noise impact (if the engines are placed above the wings)
Improved structural weight.
Twisterons work by twisting the wings during flight.
Twisting means aerodynamic washout (decreasing the camber towards wing tip) or geometric washout (decreasing angle of attack towards wing tip)
The amount of twist the Twisterons use is determined by altitude, weight and the speed the airplane is traveling
Cross-flow fan along the span of each wing.
The fan pulls the air in at the front and then expels it over the wing's trailing edge.
In transferring the work of the engine to the rotor, which spans the whole wing, the Fan Wing accelerates a large volume of air and achieves unusually high lift-efficiency.
As the name suggests
we want our aircraft to be used as fighter i.e high speed as well as bomber i.e high lift. Lets see what are conflicting mission requirements and morphing the two key word in definition.
Structures that morph their shape in response to their surroundings may at first seem like the stuff of science fiction, but take a look at nature and you will see lots of examples of plants and animals that adapt to their environment. Have you ever seen a eagle or albatross flying for hours together without flapping their wings. They change the shape and size of their wings to improve their efficiency. Tree leaves curl up in high winds to reduce their drag; bird wings bend and flex to improve their aerodynamics.
To control the camber of the aerofoil multiple actuators were used. These were distributed throughout the wings. In this figure we can see the trailing edge actuation of the wings by using the multiple actuators to vary the camber of the wing. Fibre glass flexi panels were bent by conventional rigid link mechanism. These are aerodynamically superior than conventional flaps as their were no discontinuities and seams.
Unfortunately, there were so many drawbacks. So many mechanical linkages and multiple actuators resulted in weight penalties and made the system very complex
In early 1995, during Phase I of the DARPA-funded Smart Wing Program, a variable wing camber system was investigated that employed inchworm actuators arranged in a truss manner within the wing ribs.
The other efforts investigated the effects of changing the shape of a wing using many small actuators distributed throughout a helicopter rotor or a supersonic wing.
The piezoelectric effect describes the relation between a mechanical stress and an electrical voltage in solids.
It is reversbile: an applied mechanical stress will generate a voltage and an applied voltage will change the shape of the solid by a small amount (up to a 4% change in volume).
Although in all these methods shape were changed by controlled structural deformation the flexibility of the underlying structure were not fully exploited.
In this method instead of using a plethora of actuators to locally deform a stiff structure, an alternative approach was used. The energy was drawn from a few remotely located actuators and then this energy was distributed to the structure through some intermediary mechanism. The primary design methodology employed in this effort utilized distributed compliance rather than distributed actuation
Compliant Mechanisms (Structures) are structures that are specifically optimized to distribute localized actuation (strain) to change the shape of the structure.
In this method instead of using a plethora of actuators to locally deform a stiff structure, an alternative approach was used.
. As we know all metal are elastic to some extent. Through compliant mechanism we can utilize the elasticity of underlying
In contrast, compliance is distributed to lower maximum stress, thereby significantly improve fatigue life. Just as designs in nature are strong but compliant, so are bio-inspired complaint mechanisms, which enhance “value" in a number of ways:
Just as designs in nature are strong but compliant, so are bio-inspired complaint mechanisms, which enhance “value" in a number of ways:
with modern actuators are= piezoelectric, shape-memory alloy, electro-thermal, electrostatic, fluid pressure, and electromagnetic actuators.
Materials friendly: can be built from any highly resilient material, including steel, aluminum, nickel Mission titanium alloys, polysilicon, ABS, polypropylene, polymer and metal matrix composites etc.
Weight reduction: no need for restoring springs or bulky hinges.
. Because NLF airfoils with long laminar runs have steep pressure gradients in the pressure recovery region, the gentle curvature change provided by a compliant flap can reduce or eliminate flow separation over the flap surface as opposed to a conventional hinged flap which can introduce flow separation at the flap knee.
Research is targeted at minimizing the force required to morph surfaces while maintaining maximum stiffness to withstand external loading.
The leading and trailing edge contain embedded compliant systems, consisting of a compliant mechanism, actuators, and a control system that triggers the actuators when flight conditions change.
. Comparing equally sized trailing edge flaps, MACW flaps can provide up to a 40% increase in control authority per degree deflection over hinged control surfaces
The boost in aerodynamic performance occurs not only at the aft portion where the trailing edge is located, but over the entire airfoil chord.
For instance, at zero degree AOA, the compliant flap achieves nearly a 75% increase in L/D compared to the plain hinged flap
allows the flap to be positioned with a linearly varying flap deflection along the wingspan. This has the benefit of allowing the flap to reshape the wing lift distribution closer to an elliptical distribution,
reducing the lift levels on outboard sections of the wing in order to minimize the wing
root bending moment – thus potentially saving weight. minimize the wing root bending moment – thus potentially saving weight.
compliant structures enable development of a seamless transition between the fixed and flapped portions of the wing as shown in Figure. The main purpose of this region is to reduce noise associated with the turbulent airflow generated by the discontinuous surfaces at the flap ends when the high lift flaps are deployed for landing.
One study comparing a MACW flap to a conventional trailing edge flap during a max G pull-up maneuver showed that the MACW flap required 33% less actuation force and 17% lower peak actuation power. This is because a compliant flap with 33% shorter chord than a conventional flap can provide the same CL and Cm performance.
This design paradigm of distributed compliance
While these structures have been described as “flexible,” they are optimized to resist deflection under significant external aerodynamic loading and are just as stiff and strong as a conventional control surface