It is essential that the structural stability of the aircraft wings is a major consideration in the design of the aircraft. Many studies are being carried out for the design of the wings across the globe by the researches to strengthen the aircraft wings for steady and sturdy structures for dynamic conditions. The design of the aircraft wing using NACA standards is been discussed in this work. The wing analysis is carried out by using computer numerical analysis tool, viz., CAD/CAE and CFD. The necessary inputs for carrying out the structural analysis with emphasis on the vibration are obtained by CFD analysis. The deformation of the wing structures are investigated with respect to the standard airflow velocity. The velocity of air at the inlet is taken as 122 m/s (438 km/h), considering service ceiling of 7625 m at moderate temperature. The modal analysis is considered to analyse the wing to determine the natural frequency for vibration characteristics of the wing structure. The study of the effect of the stresses and deformations of the wing structure on the vibration characteristics of the wing is carried out to understand the effect of stress on natural frequency of the aircraft wing structure. Hence it is possible to correlate the effect of wind pressure on the vibration of the wing structure for particular design of the wing (NACA). The CFD results revealed that the pressure on the upper surface of the wing for all the wing section planes (butt planes-BL) is less, about -4.97e3N/mm2, as compared to the pressure on the lower surface, about 1.08e4 N/mm2, which satisfy the theory of lift generation. The pre-stressed modal analysis shows the correlation of the stress, deformation and the corresponding mode of vibration. It is found that the maximum deformation of 17.164 mm is corresponding to the modal frequency of 179.65 Hz which can be considered as design frequency of the wing structure. However the fundamental natural frequency of the wing structure is 10.352 Hz for the deformation of 11.383 mm.
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.
Stringers are longitudinal stiffening members that support aircraft skin and prevent buckling. They transfer loads between the skin and supporting structures like frames and ribs. Stringers are commonly made of aluminum alloy and come in different cross-sectional shapes. Current research is optimizing stringer design and implementing designs in CAD software to minimize weight while ensuring strength and stability. Future work could extend the design methodology to include multiple cracks, fasteners instead of adhesive, drag forces, and design of the full wing box.
What are the elements of aircraft performance?
How much thrust do you need?
How fast and how slow can you fly?
#WikiCourses
http://wikicourses.wikispaces.com/Topic+Performance+of+aerospace+vehicles
This document provides an overview of the mechanical properties of engineering materials as presented in a lecture. It defines key terms like elasticity, plasticity, ductility, brittleness, hardness, toughness, stiffness, resilience, endurance, strength, and creep. For each property, examples are given of the types of materials that exhibit that property. The goal of the lecture is to help students understand the behavior and suitability of different materials for engineering applications by learning about their mechanical characteristics.
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.
1. An airfoil is the shape of a wing or blade that produces lift as air flows around it. It is inspired by the shape of a fish.
2. The key parts of an airfoil are the leading edge, which meets the air first, and the trailing edge, which smooths air flow.
3. NACA airfoils use a numbering system to describe characteristics like camber, thickness, and optimal lift coefficients. The 4-digit system describes camber, location of maximum camber, and thickness, while the 5-digit system provides more details.
This document discusses the structural design of aircraft. It begins by describing the basic components of an aircraft structure, including wings, fuselage, tail, and control surfaces. It then discusses the functions of different structural elements like skin, spars, ribs, stringers, and frames. It provides details on fuselage types, wing structure, empennage, landing gear, and materials used in aircraft construction. It concludes with an explanation of the V-n diagram used for structural design and load factors specified by airworthiness authorities.
The document discusses the different types and functions of aircraft fuselages. It describes how fuselages form the main body of an aircraft and house key components. There are three main types of fuselage structures: frame, monocoque, and semi-monocoque. Frame structures use a series of pipes but are heavier, while monocoque structures rely on the skin to take all loads but are fragile. Semi-monocoque fuselages provide a balance by sharing loads between the skin and internal structures. The document also outlines features like windows, doors, engines mounts and shapes that fuselages can take.
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.
Stringers are longitudinal stiffening members that support aircraft skin and prevent buckling. They transfer loads between the skin and supporting structures like frames and ribs. Stringers are commonly made of aluminum alloy and come in different cross-sectional shapes. Current research is optimizing stringer design and implementing designs in CAD software to minimize weight while ensuring strength and stability. Future work could extend the design methodology to include multiple cracks, fasteners instead of adhesive, drag forces, and design of the full wing box.
What are the elements of aircraft performance?
How much thrust do you need?
How fast and how slow can you fly?
#WikiCourses
http://wikicourses.wikispaces.com/Topic+Performance+of+aerospace+vehicles
This document provides an overview of the mechanical properties of engineering materials as presented in a lecture. It defines key terms like elasticity, plasticity, ductility, brittleness, hardness, toughness, stiffness, resilience, endurance, strength, and creep. For each property, examples are given of the types of materials that exhibit that property. The goal of the lecture is to help students understand the behavior and suitability of different materials for engineering applications by learning about their mechanical characteristics.
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.
1. An airfoil is the shape of a wing or blade that produces lift as air flows around it. It is inspired by the shape of a fish.
2. The key parts of an airfoil are the leading edge, which meets the air first, and the trailing edge, which smooths air flow.
3. NACA airfoils use a numbering system to describe characteristics like camber, thickness, and optimal lift coefficients. The 4-digit system describes camber, location of maximum camber, and thickness, while the 5-digit system provides more details.
This document discusses the structural design of aircraft. It begins by describing the basic components of an aircraft structure, including wings, fuselage, tail, and control surfaces. It then discusses the functions of different structural elements like skin, spars, ribs, stringers, and frames. It provides details on fuselage types, wing structure, empennage, landing gear, and materials used in aircraft construction. It concludes with an explanation of the V-n diagram used for structural design and load factors specified by airworthiness authorities.
The document discusses the different types and functions of aircraft fuselages. It describes how fuselages form the main body of an aircraft and house key components. There are three main types of fuselage structures: frame, monocoque, and semi-monocoque. Frame structures use a series of pipes but are heavier, while monocoque structures rely on the skin to take all loads but are fragile. Semi-monocoque fuselages provide a balance by sharing loads between the skin and internal structures. The document also outlines features like windows, doors, engines mounts and shapes that fuselages can take.
For Video Lecture of this presentation: https://youtu.be/8sMbl6pJpd0
The topics covered in this session are, Primary flight instruments: Altimeter, ASI (Airspeed Indicator ), VSI (vertical speed indicator) , Turn-bank indicator. The session is categorized into two portions namely, pitot-static system based and gyroscopic instrument based.
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 provides an overview of aircraft structures and their key components. It discusses the fuselage, wings, empennage, landing gear, and powerplants. For each component, it describes the basic design and functions. It also covers important aircraft structural concepts like stressed skin construction, monocoque vs semi-monocoque design, and choices of lightweight metal materials. Overall the document serves as a high-level introduction to aircraft structures and the major structural components of airplanes.
Classification of Aircraft | Flight Mechanics | GATE AerospaceAge of Aerospace
This document provides an overview of aircraft classification. It discusses how aircraft can be classified based on their lift generation, propulsion system, speed, purpose, size, and other characteristics. The core classifications are lighter-than-air aircraft such as balloons and airships, and heavier-than-air aircraft like airplanes, helicopters, and ornithopters. Within these groups, aircraft are further classified by attributes including their engine type, intended use, passenger/cargo capacity, power source, wing configuration, and range. Special aircraft types are also outlined.
This document summarizes a presentation given by the FAASTeam to pilots and instructors on stall and spin awareness and avoidance. The presentation covers topics like normal and crosswind takeoffs, slow flight, steep turns, stalls, landings, and go-arounds. It discusses common errors during these maneuvers, such as improper pitch control, failure to maintain a stabilized approach, and inadequate compensation for wind. The goal is to help pilots identify strengths and weaknesses and reduce the risk of accidents during takeoff, landing, and low-altitude maneuvering. Quizzes are included to reinforce key concepts.
Atmosphere: Properties and Standard Atmosphere | Flight Mechanics | GATE Aero...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/DqaoNt0LoIE
The topics covered in this session are, Properties of Atmosphere, International Standard Atmosphere (ISA) definition and derivation, ISA Chart. The formula for obtaining ISA Chartar completely derived from basic equations.
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
Takeoff and Landing | Flight Mechanics | GATE AerospaceAge of Aerospace
This document provides an overview of the topics covered in a presentation on flight mechanics, takeoff, and landing. The core topics include basics of atmosphere, aircraft classification, airplane configuration, flight instruments, aerodynamic forces, and airplane performance including takeoff, landing, climb, descent, stability, and equations of motion. The presentation will focus on takeoff and landing performance, outlining the different segments of ground roll for takeoff and approach/flare/ground roll distances for landing, as well as factors that influence accelerated performance like drag, minimum control speeds, and decision speeds. References for further information are provided.
The document discusses the major components of aircraft, including the fuselage, wings, empennage, landing gear, and power plant. It describes the construction and design of aircraft fuselages, including open truss, monocoque, and semi-monocoque structures. It also briefly discusses wings, the empennage, landing gear, and factors considered in aircraft component design like fatigue life and material selection.
The document discusses aircraft landing gear, including:
1) The main functions of landing gear such as supporting the aircraft's weight and absorbing landing shocks.
2) The basic types of landing gear including fixed, retractable, and types based on arrangement like single, double, and tandem.
3) Key components of landing gear like shock struts, torque links, and the various actuators, links, and mechanisms involved.
Airspeeds | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, Formulae and topic wise Solutions for the topic "Airspeeds" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
The document discusses materials used for aircrafts and how they have evolved over time. It begins by providing background on the Indian aviation industry and objectives for aircraft materials such as maximizing strength while minimizing mass. Various materials are then examined, including wood in early planes, steel and duralumin in early 20th century planes, aluminum and titanium in subsonic and supersonic planes, and increasing use of composites such as fiberglass and carbon fiber composites in modern planes like the Boeing 787 and India's Tejas aircraft. Composites provide benefits like reduced weight, improved efficiency and lower assembly time.
Airplane (fixed wing aircraft) configuration and various parts | Flight Mecha...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/uD_qWvTZEhY
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
There are several types of drag that oppose the forward motion of an aircraft:
1) Form drag is caused by the shape of the aircraft and separation of air flowing over it. Skin friction drag results from air particles contacting the aircraft surface.
2) Induced drag is caused by lift and increases with angle of attack. It varies inversely with airspeed.
3) Parasitic drag includes form and skin friction drag and increases with airspeed. Wave drag occurs above the speed of sound due to shock waves.
4) Induced drag dominates at low speeds while parasitic drag increases rapidly at high speeds. Total drag equals parasitic plus induced drag. Drag decreases with reduced air density at higher altitudes.
For Video Lecture of this presentation: https://youtu.be/u7bp9IJqRVM
The topics covered in this session are, Slip: Types of slip, Sideslip angle, Sideslip angle sign conventions, restoring yaw moments, physical significance, Calculation of sideslip angle, Measurement of sideslip.
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 document discusses two-dimensional vector variable problems in structural mechanics. It describes plane stress, plane strain and axisymmetric problems, and provides the stress-strain relations for materials under these conditions. It also discusses thin structures like disks and long prismatic shafts. Additionally, it covers dynamic analysis and vibration of structures, describing free vibration, forced vibration and types of vibration. Equations of motion are developed using Lagrange's approach and the weak form method. Mass and stiffness matrices for axial rod and beam elements are also presented.
Design and analysis of wing for Unmanned Aerial Vehicle using CFDPranit Dhole
Unmanned Aerial Vehicle (UAV) is an important technology for military and security application. Various missions can be done using UAV such as surveillance in unknown areas, forestry conservation, and spying enemy territory. Selection of components such as aerofoil plays huge roll in performers of UAV in terms of lift, drag, load carrying capacity, range etc.
This project presents an approach for designing of wing by selecting proper aerofoil and CFD analysis for verifying aerodynamics characteristics.
Aircraft rigging, levelling and jacking systemPriyankaKg4
The document outlines safety procedures for jacking up an aircraft for maintenance. A coordinator should supervise as technicians jack up the aircraft at designated points, checking that its weight, fuel levels, and center of gravity are within specifications. The aircraft should be positioned inside a hangar on level ground protected from wind, with chocks in front of and behind the wheels and brakes released. Clearance and space for equipment must be ensured around the aircraft.
Structural detailing of fuselage of aeroplane /aircraft.PriyankaKg4
This presentation is about the structural detailing of fuselage of aeroplane .The fuselage or body of the airplane, holds all the pieces together. The pilots sit in the cockpit at the front of the fuselage. Passengers and cargo are carried in the rear of the fuselage. Some aircraft carry fuel in the fuselage; others carry the fuel in the wings.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
Static and Dynamic Analysis of Floor Beam (Cross beam) of AircraftIRJET Journal
This document summarizes a study analyzing the static and dynamic behavior of floor beams used in aircraft. Floor beams experience bending stresses and support the weight of the aircraft. The researchers modeled a floor beam in CATIA and analyzed it in ANSYS to study stresses under different loads. They also analyzed a carbon fiber reinforced plastic floor beam. Modal analysis determined the beam's natural frequencies under vibration to ensure it can withstand operating conditions. The study aims to optimize floor beam design and materials to reduce weight while maintaining strength.
For Video Lecture of this presentation: https://youtu.be/8sMbl6pJpd0
The topics covered in this session are, Primary flight instruments: Altimeter, ASI (Airspeed Indicator ), VSI (vertical speed indicator) , Turn-bank indicator. The session is categorized into two portions namely, pitot-static system based and gyroscopic instrument based.
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 provides an overview of aircraft structures and their key components. It discusses the fuselage, wings, empennage, landing gear, and powerplants. For each component, it describes the basic design and functions. It also covers important aircraft structural concepts like stressed skin construction, monocoque vs semi-monocoque design, and choices of lightweight metal materials. Overall the document serves as a high-level introduction to aircraft structures and the major structural components of airplanes.
Classification of Aircraft | Flight Mechanics | GATE AerospaceAge of Aerospace
This document provides an overview of aircraft classification. It discusses how aircraft can be classified based on their lift generation, propulsion system, speed, purpose, size, and other characteristics. The core classifications are lighter-than-air aircraft such as balloons and airships, and heavier-than-air aircraft like airplanes, helicopters, and ornithopters. Within these groups, aircraft are further classified by attributes including their engine type, intended use, passenger/cargo capacity, power source, wing configuration, and range. Special aircraft types are also outlined.
This document summarizes a presentation given by the FAASTeam to pilots and instructors on stall and spin awareness and avoidance. The presentation covers topics like normal and crosswind takeoffs, slow flight, steep turns, stalls, landings, and go-arounds. It discusses common errors during these maneuvers, such as improper pitch control, failure to maintain a stabilized approach, and inadequate compensation for wind. The goal is to help pilots identify strengths and weaknesses and reduce the risk of accidents during takeoff, landing, and low-altitude maneuvering. Quizzes are included to reinforce key concepts.
Atmosphere: Properties and Standard Atmosphere | Flight Mechanics | GATE Aero...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/DqaoNt0LoIE
The topics covered in this session are, Properties of Atmosphere, International Standard Atmosphere (ISA) definition and derivation, ISA Chart. The formula for obtaining ISA Chartar completely derived from basic equations.
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
Takeoff and Landing | Flight Mechanics | GATE AerospaceAge of Aerospace
This document provides an overview of the topics covered in a presentation on flight mechanics, takeoff, and landing. The core topics include basics of atmosphere, aircraft classification, airplane configuration, flight instruments, aerodynamic forces, and airplane performance including takeoff, landing, climb, descent, stability, and equations of motion. The presentation will focus on takeoff and landing performance, outlining the different segments of ground roll for takeoff and approach/flare/ground roll distances for landing, as well as factors that influence accelerated performance like drag, minimum control speeds, and decision speeds. References for further information are provided.
The document discusses the major components of aircraft, including the fuselage, wings, empennage, landing gear, and power plant. It describes the construction and design of aircraft fuselages, including open truss, monocoque, and semi-monocoque structures. It also briefly discusses wings, the empennage, landing gear, and factors considered in aircraft component design like fatigue life and material selection.
The document discusses aircraft landing gear, including:
1) The main functions of landing gear such as supporting the aircraft's weight and absorbing landing shocks.
2) The basic types of landing gear including fixed, retractable, and types based on arrangement like single, double, and tandem.
3) Key components of landing gear like shock struts, torque links, and the various actuators, links, and mechanisms involved.
Airspeeds | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, Formulae and topic wise Solutions for the topic "Airspeeds" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
The document discusses materials used for aircrafts and how they have evolved over time. It begins by providing background on the Indian aviation industry and objectives for aircraft materials such as maximizing strength while minimizing mass. Various materials are then examined, including wood in early planes, steel and duralumin in early 20th century planes, aluminum and titanium in subsonic and supersonic planes, and increasing use of composites such as fiberglass and carbon fiber composites in modern planes like the Boeing 787 and India's Tejas aircraft. Composites provide benefits like reduced weight, improved efficiency and lower assembly time.
Airplane (fixed wing aircraft) configuration and various parts | Flight Mecha...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/uD_qWvTZEhY
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
There are several types of drag that oppose the forward motion of an aircraft:
1) Form drag is caused by the shape of the aircraft and separation of air flowing over it. Skin friction drag results from air particles contacting the aircraft surface.
2) Induced drag is caused by lift and increases with angle of attack. It varies inversely with airspeed.
3) Parasitic drag includes form and skin friction drag and increases with airspeed. Wave drag occurs above the speed of sound due to shock waves.
4) Induced drag dominates at low speeds while parasitic drag increases rapidly at high speeds. Total drag equals parasitic plus induced drag. Drag decreases with reduced air density at higher altitudes.
For Video Lecture of this presentation: https://youtu.be/u7bp9IJqRVM
The topics covered in this session are, Slip: Types of slip, Sideslip angle, Sideslip angle sign conventions, restoring yaw moments, physical significance, Calculation of sideslip angle, Measurement of sideslip.
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 document discusses two-dimensional vector variable problems in structural mechanics. It describes plane stress, plane strain and axisymmetric problems, and provides the stress-strain relations for materials under these conditions. It also discusses thin structures like disks and long prismatic shafts. Additionally, it covers dynamic analysis and vibration of structures, describing free vibration, forced vibration and types of vibration. Equations of motion are developed using Lagrange's approach and the weak form method. Mass and stiffness matrices for axial rod and beam elements are also presented.
Design and analysis of wing for Unmanned Aerial Vehicle using CFDPranit Dhole
Unmanned Aerial Vehicle (UAV) is an important technology for military and security application. Various missions can be done using UAV such as surveillance in unknown areas, forestry conservation, and spying enemy territory. Selection of components such as aerofoil plays huge roll in performers of UAV in terms of lift, drag, load carrying capacity, range etc.
This project presents an approach for designing of wing by selecting proper aerofoil and CFD analysis for verifying aerodynamics characteristics.
Aircraft rigging, levelling and jacking systemPriyankaKg4
The document outlines safety procedures for jacking up an aircraft for maintenance. A coordinator should supervise as technicians jack up the aircraft at designated points, checking that its weight, fuel levels, and center of gravity are within specifications. The aircraft should be positioned inside a hangar on level ground protected from wind, with chocks in front of and behind the wheels and brakes released. Clearance and space for equipment must be ensured around the aircraft.
Structural detailing of fuselage of aeroplane /aircraft.PriyankaKg4
This presentation is about the structural detailing of fuselage of aeroplane .The fuselage or body of the airplane, holds all the pieces together. The pilots sit in the cockpit at the front of the fuselage. Passengers and cargo are carried in the rear of the fuselage. Some aircraft carry fuel in the fuselage; others carry the fuel in the wings.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
Static and Dynamic Analysis of Floor Beam (Cross beam) of AircraftIRJET Journal
This document summarizes a study analyzing the static and dynamic behavior of floor beams used in aircraft. Floor beams experience bending stresses and support the weight of the aircraft. The researchers modeled a floor beam in CATIA and analyzed it in ANSYS to study stresses under different loads. They also analyzed a carbon fiber reinforced plastic floor beam. Modal analysis determined the beam's natural frequencies under vibration to ensure it can withstand operating conditions. The study aims to optimize floor beam design and materials to reduce weight while maintaining strength.
IRJET- Particle Swarm Intelligence based Dynamics Economic Dispatch with Dail...IRJET Journal
This document presents a structural and modal analysis of the wing of a subsonic aircraft using ANSYS Workbench. The study analyzes the wing structure made of two materials, aluminum alloy and titanium alloy, under a pressure load of 500 Pa to determine which is best suited. A 3D model of the wing is created based on the NACA 4412 airfoil dimensions and meshed. Boundary conditions fixing one end and applying pressure are applied. For each material, the total deformation, equivalent stress, maximum principle stress, and equivalent strain are determined from the static structural analysis and compared to select the best material for withstanding the loads in wing design.
This document discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
This document discusses weight optimization of the vertical tail in-board box structure of an aircraft through stress analysis. The vertical tail structure is modeled in CATIA and imported into MSC Patran for finite element analysis. The structure is meshed and material properties are applied. Boundary conditions representing the fixed root and free top surface are applied. Stress analysis is performed and high stress regions are identified. An iterative approach is used to introduce lightening cutouts in the spar and rib webs to reduce weight. Two iterations are performed, reducing the total weight by 1.66kg while maintaining similar deformation levels and stresses below material yield strength, demonstrating an effective weight optimization approach.
This document presents a methodology for performing static structural analysis of fighter aircraft wing spars to identify critical stresses. It involves calculating bending, shear and von mises stresses analytically and numerically under different loading conditions. CAD models of the wing and spars are imported into ANSYS for finite element analysis. Von Mises yield theory is used to identify stresses exceeding the yield limit, which indicate critical stresses and locations. Results from analytical calculations and ANSYS simulations are analyzed to mark stresses exceeding the safety factor of 1.5 as critical. Locations with critical stresses are identified as the attachment points of wing spars.
Flow Anlaysis on Hal Tejas Aircraft using Computational Fluid Dynamics with D...IJAEMSJORNAL
In the current globalization, we can see many innovations being introduced or implemented in every aspect of field that are considered to be existed. Every country is aiming to develop its power over all the aspects that considered for comparison with other countries in order to stand at same level of competition with others. One such power considered by all countries to develop every possible way to have a healthy competition is the military power which involves basically innovations of fast moving aircraft having a high lift coefficient and low drag coefficient. Such an aircraft having the high lift and low drag coefficient is TEJAS (HAL) developed by country India on which the purpose of paper mainly sustains. The paper mainly focuses on steady-state flow analysis over aircraft TEJAS using the computer aided modelling techniques and also the comparison of the results obtained from the modelled techniques. The paper also outlines the designing of the structural model of the TEJAS in a modelling software, creation of a finite computational domain, segmentation of this domain into discrete intervals, applying boundary conditions such as velocity in order to obtain plots and desired results determining the coefficient of pressure, lift and drag coefficient, velocity magnitude etc. This paper also aims in creating awareness to the future students about the techniques involved and knowledge required for developing a designed modelled. This paper also highlights the use of CFD techniques involved for the purpose of fluid flow simulation of the aircraft especially performing the meshing techniques, pre and post processing techniques and finally the evaluation of the simulation. Finally this paper can be seen as source by future generation students in gaining knowledge about design, analysis and simulation of the structured model on various conditions, about the field of aerospace engineering and new innovations being developed and also about the career involved when the above fields were chosen foe specialization purposes
IRJET- Static and Fracture Analysis for Aircraft Fuselage and Wing Joint with...IRJET Journal
This document discusses static and fracture analysis of aircraft fuselage and wing joints using composite materials. Finite element analysis software ANSYS and a post-processing program called 3MBSIF are used to determine stress intensity factors for cracks in longitudinal and circumferential fuselage joints under internal pressure loading. Residual strength is predicted using strain energy density theory of fracture. Fatigue life is represented using the Goodman curve. The structural component is designed and analyzed in CREO and ANSYS to calculate stresses and determine fatigue life for different loading conditions.
A Study on Damage Tolerance Evaluation of the Vertical Tail with the Z stiffe...IRJET Journal
This document discusses damage tolerance evaluation of the vertical tail with a stiffened panel on a transport aircraft. It begins with an introduction to aircraft structures and importance of vertical tails. Then it describes the stiffened panel that will be analyzed which makes up part of the vertical tail. Finite element analysis is performed to identify stress concentrations on the panel. A crack is initiated at the location of maximum stress and crack growth analysis is performed to evaluate the panel's damage tolerance capabilities. Stress intensity factors at the crack tip are calculated using the modified virtual crack closure integral method and compared to fracture toughness to assess crack growth.
IRJET- Numerical Analysis of Nose Landing Gear SystemIRJET Journal
This document presents a numerical analysis of the nose landing gear system of an aircraft using finite element analysis. It begins with an abstract that outlines the objective to determine stress behavior and displacement of the nose gear during landing. It then describes the modeling process where the nose gear was modeled in CAD software and imported into finite element analysis software for meshing and application of loads and constraints. Key steps of the finite element analysis are described including discretization, deriving element equations, assembling global equations, applying loads/boundaries, and solving for results. Results of the finite element analysis such as stress contours, displacement contours, and natural frequencies are presented and discussed.
Structural Analysis and Optimization for Spar Beam of an AircraftIRJET Journal
This document summarizes a study analyzing and optimizing the structural design of a tapered spar beam for an aircraft wing. The study involved creating a geometric model of the spar beam, applying loads and boundary conditions representative of flight loading, conducting a finite element analysis to determine stresses and displacements, and performing topological optimization to reduce weight. Key results were stresses of up to 38 MPa at the fixed end of the beam, displacements of up to 3.1 mm at the free end, and a 40% reduction in web weight achieved through topological optimization while maintaining structural integrity. The optimized design demonstrated potential to strengthen the spar beam structure while reducing material usage and weight.
Design and Finite Element Analysis of Aircraft Wing using Ribs and SparsIRJET Journal
This document describes the design and finite element analysis of an aircraft wing structure using ribs and spars. The wing structure was modeled in PRO-ENGINEER and then analyzed in ANSYS. Static, fatigue, and modal analyses were performed to determine stresses, life, damage, and deformation under different loads and speeds. The analyses showed that a carbon epoxy composite material performed better than aluminum or glass materials, with lower stresses and higher safety factors. In conclusion, the carbon epoxy material was determined to be better suited for aircraft wings.
Optimizationof fuselage shape for better pressurization and drag reductioneSAT Journals
Abstract
The fuselage of any aircraft is essentially to accommodate the payload. It is normally not as streamlined as the wing. Cabin pressurization has been a major concern in the manufacturing of aircrafts. Generally, a cylindrical shape is preferred from a pressurization point of view as it has a higher strength and weighs less too. On the other hand, a sphere is considered as the best pressure vessel among all the shapes, but, sphere being a bluff body is not suitable for carrying payloads. On this note, a cylinder is considered to be better than a sphere to carry the payload and mainly to achieve a streamlined flow. In this paper, the shape chosen is a combination of the sphere and the cylinder to achieve optimum results for pressurization as well as a better streamlined flow. Our prime aim is to convert this bluff body into something more efficient and useful, rather than only for carrying the payload. We have focused basically on two details viz. 1) Better Pressurization and 2) to assist in minimizing the drag, thereby increasing the overall lift of the aircraft and hence increasing the fuel efficiency. The proposed fuselage structure was designed in CATIA V5 software and structural analyses were done in Auto-Desk Multi-Physics software. As a result, a better structural load capacity was found. A load of 10 N/mm2 was applied on both the bodies under consideration (cylinder and ellipse) having the same material, surface area, volume and weight. For the proposed elliptical design, 78% reduction in the minimum stress value and 10% reduction in the maximum stress value were noticed.
Keywords: Fuselage, Lifting Fuselage, Drag Reduction, Pressurization, Hoop Stress, Multi body design, Toroidal Shells, Multi-cylinder, Channel Propeller Configuration, Carbon Fiber, Graphite Fiber, Stabilization and Carbonization.
Design, Fabrication and Aerodynamic Analysis of RC Powered Aircraft WingIRJET Journal
This document describes the design, fabrication, and aerodynamic analysis of a radio-controlled aircraft wing. The researchers designed a rectangular wing with a Gottingen 526 airfoil profile using computational fluid dynamics software to analyze lift and drag coefficients. The wing structure and control surfaces were fabricated based on the optimal design parameters. Wind tunnel testing was then used to validate the aerodynamic performance and characteristics of the wing.
Design, Analysis and Testing of Wing Spar for Optimum WeightRSIS International
Aircraft is a complex mechanical structure with flying capability. The structure of an airframe represents one of the finest examples of a minimum weight design in the field of structural engineering. Surprisingly such an efficient design is achieved by the use of simple “strength-of-material” approach. Aircraft has two major components, which are fuselage and wing. For a wing of an aircraft the primary load carrying ability is required in bending. A typical aluminium material 6082-T6 is chosen for the design. A four-Seater aircraft wing spar design is considered in the current study. Wings of the aircraft are normally attached to the fuselage at the root of the wing. This makes the wing spar beam to behave almost like a cantilever beam. Minimum two spars are considered in the wing design. In a conventional beam design approach one will end up in heavy weight for the spar of the wing. In the current project the spar is considered as a beam with discrete loads at different stations. The design is carried out as per the external bending moment at each station. A finite element approach is used to calculate the stresses developed at each station for a given bending moment. Several stress analysis iterations are carried out for design optimization of the spar beam. Linear static analysis is used for the stress analysis. The spar beam is designed to yield at the design limit load. Weight optimization of the spar will be carried out by introducing lightening cut-outs in the web region. The results from the conventional design approach and the optimized design are compared. Weight saving through the design optimization is calculated. Spar will be a built-up structure. A scale-down model of the spar will be fabricated using aluminium alloy 6082-T6 material. Static testing of the spar will be carried out to validate the design and stress analysis results.
1) The document describes the design of a dragonfly-inspired aircraft with two different wing configurations: an elliptical wing and a forward-swept wing.
2) The design process involved taking measurements from existing aircraft like the Sukhoi-47, X-29, and Supermarine Spitfire to inform the conceptual and detailed design of the dragonfly aircraft.
3) CFD analysis of the 2D aircraft model showed that the unique dual-wing configuration is capable of producing lift, indicating that the design could potentially fly. The analysis paves the way for future dual-wing aircraft designs.
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.
Similar to Study of Aircraft Wing with Emphasis on Vibration Characteristics (20)
Understanding Inductive Bias in Machine LearningSUTEJAS
This presentation explores the concept of inductive bias in machine learning. It explains how algorithms come with built-in assumptions and preferences that guide the learning process. You'll learn about the different types of inductive bias and how they can impact the performance and generalizability of machine learning models.
The presentation also covers the positive and negative aspects of inductive bias, along with strategies for mitigating potential drawbacks. We'll explore examples of how bias manifests in algorithms like neural networks and decision trees.
By understanding inductive bias, you can gain valuable insights into how machine learning models work and make informed decisions when building and deploying them.
Using recycled concrete aggregates (RCA) for pavements is crucial to achieving sustainability. Implementing RCA for new pavement can minimize carbon footprint, conserve natural resources, reduce harmful emissions, and lower life cycle costs. Compared to natural aggregate (NA), RCA pavement has fewer comprehensive studies and sustainability assessments.
ACEP Magazine edition 4th launched on 05.06.2024Rahul
This document provides information about the third edition of the magazine "Sthapatya" published by the Association of Civil Engineers (Practicing) Aurangabad. It includes messages from current and past presidents of ACEP, memories and photos from past ACEP events, information on life time achievement awards given by ACEP, and a technical article on concrete maintenance, repairs and strengthening. The document highlights activities of ACEP and provides a technical educational article for members.
CHINA’S GEO-ECONOMIC OUTREACH IN CENTRAL ASIAN COUNTRIES AND FUTURE PROSPECTjpsjournal1
The rivalry between prominent international actors for dominance over Central Asia's hydrocarbon
reserves and the ancient silk trade route, along with China's diplomatic endeavours in the area, has been
referred to as the "New Great Game." This research centres on the power struggle, considering
geopolitical, geostrategic, and geoeconomic variables. Topics including trade, political hegemony, oil
politics, and conventional and nontraditional security are all explored and explained by the researcher.
Using Mackinder's Heartland, Spykman Rimland, and Hegemonic Stability theories, examines China's role
in Central Asia. This study adheres to the empirical epistemological method and has taken care of
objectivity. This study analyze primary and secondary research documents critically to elaborate role of
china’s geo economic outreach in central Asian countries and its future prospect. China is thriving in trade,
pipeline politics, and winning states, according to this study, thanks to important instruments like the
Shanghai Cooperation Organisation and the Belt and Road Economic Initiative. According to this study,
China is seeing significant success in commerce, pipeline politics, and gaining influence on other
governments. This success may be attributed to the effective utilisation of key tools such as the Shanghai
Cooperation Organisation and the Belt and Road Economic Initiative.
Electric vehicle and photovoltaic advanced roles in enhancing the financial p...IJECEIAES
Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
Using recycled concrete aggregates (RCA) for pavements is crucial to achieving sustainability. Implementing RCA for new pavement can minimize carbon footprint, conserve natural resources, reduce harmful emissions, and lower life cycle costs. Compared to natural aggregate (NA), RCA pavement has fewer comprehensive studies and sustainability assessments.
Redefining brain tumor segmentation: a cutting-edge convolutional neural netw...IJECEIAES
Medical image analysis has witnessed significant advancements with deep learning techniques. In the domain of brain tumor segmentation, the ability to
precisely delineate tumor boundaries from magnetic resonance imaging (MRI)
scans holds profound implications for diagnosis. This study presents an ensemble convolutional neural network (CNN) with transfer learning, integrating
the state-of-the-art Deeplabv3+ architecture with the ResNet18 backbone. The
model is rigorously trained and evaluated, exhibiting remarkable performance
metrics, including an impressive global accuracy of 99.286%, a high-class accuracy of 82.191%, a mean intersection over union (IoU) of 79.900%, a weighted
IoU of 98.620%, and a Boundary F1 (BF) score of 83.303%. Notably, a detailed comparative analysis with existing methods showcases the superiority of
our proposed model. These findings underscore the model’s competence in precise brain tumor localization, underscoring its potential to revolutionize medical
image analysis and enhance healthcare outcomes. This research paves the way
for future exploration and optimization of advanced CNN models in medical
imaging, emphasizing addressing false positives and resource efficiency.
A review on techniques and modelling methodologies used for checking electrom...nooriasukmaningtyas
The proper function of the integrated circuit (IC) in an inhibiting electromagnetic environment has always been a serious concern throughout the decades of revolution in the world of electronics, from disjunct devices to today’s integrated circuit technology, where billions of transistors are combined on a single chip. The automotive industry and smart vehicles in particular, are confronting design issues such as being prone to electromagnetic interference (EMI). Electronic control devices calculate incorrect outputs because of EMI and sensors give misleading values which can prove fatal in case of automotives. In this paper, the authors have non exhaustively tried to review research work concerned with the investigation of EMI in ICs and prediction of this EMI using various modelling methodologies and measurement setups.
Study of Aircraft Wing with Emphasis on Vibration Characteristics
1. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 1 | P a g e
Study of Aircraft Wing with Emphasis on Vibration
Characteristics
Nataraj Kuntoji*, Dr. Vinay V. Kuppast**
* M.Tech Student, Department of Mechanical Engineering, Basaveshwar Engineering College, (Affl. to
Visvesvaraya Technological University, Belgaum) Bagalkot, India
Email: nataraj.kuntoji@gmail.com
** Professor, Department of Mechanical Engineering, Basaveshwar Engineering College, (Affl. to Visvesvaraya
Technological University, Belgaum) Bagalkot, India
Email: vinay_kuppast@yahoo.com
ABSTRACT
It is essential that the structural stability of the aircraft wings is a major consideration in the design of the
aircraft. Many studies are being carried out for the design of the wings across the globe by the researches to
strengthen the aircraft wings for steady and sturdy structures for dynamic conditions.
The design of the aircraft wing using NACA standards is been discussed in this work. The wing analysis is
carried out by using computer numerical analysis tool, viz., CAD/CAE and CFD. The necessary inputs for
carrying out the structural analysis with emphasis on the vibration are obtained by CFD analysis. The
deformation of the wing structures are investigated with respect to the standard airflow velocity. The velocity of
air at the inlet is taken as 122 m/s (438 km/h), considering service ceiling of 7625 m at moderate temperature.
The modal analysis is considered to analyse the wing to determine the natural frequency for vibration
characteristics of the wing structure. The study of the effect of the stresses and deformations of the wing
structure on the vibration characteristics of the wing is carried out to understand the effect of stress on natural
frequency of the aircraft wing structure. Hence it is possible to correlate the effect of wind pressure on the
vibration of the wing structure for particular design of the wing (NACA).
The CFD results revealed that the pressure on the upper surface of the wing for all the wing section planes (butt
planes-BL) is less, about -4.97e3N/mm2, as compared to the pressure on the lower surface, about 1.08e4
N/mm2, which satisfy the theory of lift generation. The pre-stressed modal analysis shows the correlation of the
stress, deformation and the corresponding mode of vibration. It is found that the maximum deformation of
17.164 mm is corresponding to the modal frequency of 179.65 Hz which can be considered as design frequency
of the wing structure. However the fundamental natural frequency of the wing structure is 10.352 Hz for the
deformation of 11.383 mm.
Keywords: Structural analysis, Modal analysis, CATIA V5R19, CFD
I. INTRODUCTION
Aircraft to fly successfully in air depends on four
aerodynamic forcesthey are thrust, drag, gravity
and lift. Thrust is the forward speed of the plane.
Drag is a backward force exerted on the plane, a
result of the friction between aircraft wing and air.
Lift is the upward force acting on the plane. Weight
of the aircraft itself is considered as gravity. Lift and
gravity is one pair of opposing forces; thrust and
drag is another pair of opposing forces. If thrust
must exceed the level of drag the plane will move
faster, similarly lift must exceed gravity to go up.
The predominant function of the aircraft wing is to
generate sufficient lift (L). Drag (D) and nose-down
pitching moment (M) are the two other components
of wing. The main primary aim of the wing design is
to maximize the lift and minimize the other two
components. The wing is considered as a lifting
surface and works on lift generation theory, that lift
is produced due to the pressure difference between
lower and upper surfaces.
The particular wing design depends upon
many factors for example, size, weight, use of the
aircraft, desired landing speed, and desired rate of
climb. In some aircraft, the larger compartments of
the wings are used as fuel tanks. The wings are
designated as right and left, corresponding to the
right- and left-hand sides of a pilot seated in the
aircraft.
RESEARCH ARTICLE OPEN ACCESS
2. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 2 | P a g e
Fig 1: Wing construction
One method of wing construction is shown
in Fig.1 [1]. In this illustration, two main spars are
used with ribs placed at frequent intervals between
the spars to develop the wing contour. This is called
"two-spar" construction. Other variations of wing
construction include "mono spar (open spar), multi
spar (three or more spars), and box beam." In the
box beam construction, the stringers and spar like
sections are joined together in a box-shaped beam.
Then the remainder of the wing is constructed
around the box.
The skin is attached to all the structural
members and carries part of the wing loads and
stresses. During flight, the loads imposed on the
wing structure act primarily on the skin. From the
skin, the loads are transmitted to the ribs and then to
the spars. The spars support all distributed loads as
well concentrated weights, such as a fuselage,
landing gear, and nacelle. Corrugated sheet
aluminum alloy is often used as a sub covering for
wing structures. The Lockheed P-3 Orion wing is an
example of this type of construction. Inspection and
access panels are usually provided on the lower
surface of a wing. Drain holes are also placed in the
lower surfaces. Walkways are provided on the areas
of the wing where personnel should walk or step.
The substructure is stiffened or reinforced in the
vicinity of the walkways to take such loads.
Walkways are usually covered with a nonskid
surface. Some aircraft have no built-in walkways. In
these cases removable mats or covers are used to
protect the wing surface. On some aircraft, jacking
points are provided on the underside of each wing.
The jacking points may also be used as tie down
fittings for securing the aircraft.
If the aircraft is large station numbering
system is used to locate large assemblies, such as
fuselage stations (FS) measured along the length of
the aircraft, increasing from nose tip to tail.
Generally station 0 is somewhere in front of the
airplane. Water lines (WL) measured along the
height of the aircraft, from ground up. Butt lines
(BL) are measured either side of the aircraft and
centerline is considered as mid of the airplane. A
butt line represents the stations along the wing as
shown in Fig.2.
Fig.2: Wing station lines
The specifications used in the design of General
Mooney M20TN Acclaim are considered as the
input to the present work [2].
II. LITERATURE REVIEW
The purpose of the literature survey is to
study the works of different researchers concerned
with the detailed study of the air craft wing design.
Also to find out the scope for any new methods of
design by which the design process is made simple,
robust, less time consuming and cost effective. The
literature survey is entirely based on the previous
research methods. It is desired to explore the
application of the fundamental properties such as
vibration which plays an important role in the failure
of the structure. Hence the literature survey is
carried out emphasizing the structural design of the
aircraft wing subjected to vibration.
Design of aircraft wing is totally depends
on airfoil design or selection, during the 1930's
several families of airfoils and camber lines were
developed by the NACA was a U.S. federal agency.
NASA Langley Research Centre sponsored the
development of computer programs for generation of
ordinates of standard NACA airfoils. Existing airfoil
sections can be selected easily for referring to the .N.
Jacobs, K.E. Ward, & R.M. Pinkerton. NACA
Report No. 460. [3]
Several researchers expressed their view
regarding difficulty in solving analytically the
aerodynamic problems. Huge experimental expenses
are involved in solving aerodynamic problems.
Hence they preferred numerical methods. Nguyen
Minh Triet et.al in their paper digitally (using
CAD,CAE and CFD) calculated the lift and drag
forces by varying the inlet velocity from 0 to 50 m/s
results were compared with the theoretical results.[4]
Kakumani Sureka and R Satya Meher in
their paper they modelled A300 aircraft wing using
standard NACA 64215 airfoil with spars and ribs
3. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 3 | P a g e
digitally using different materials. They arrived to
the conclusion that Aluminium alloy 7068 is
preferred over Aluminium alloy in order to give the
more strength to the structure. [5]
Sudhir Reddy Konayapalli and Y Sujatha
discussed the aircraft wing design. They concluded
that static pressure was increased with increase in
the angle of attack. Dynamic pressure on lower
surface was decreasing with increasing angle of
attack whereas static pressure was increasing on
lower surface [6]
Lica Flore and Albert Arnau Cubillo
presented the results of the dynamical behaviour on
an aircraft wing structure. The study has consisted
strain gauges to test aircraft wing dynamically in
which the vibration parameters of the structure have
been determined. [7]
Farrukh Mazhar and Abdul Munem Khan
were used implicit CAD model and aerodynamic
CFD analysis of the vehicle as design input, and
employing Artificial Neural Networks they
concluded that the wing made up of composite
material was lighter in weight as compared to a
similar wing made from aluminium, and sufficiently
strong enough to meet all in-flight load conditions
and factor of safety. [8]
III. CAD MODELLING OF AIRCRAFT
WING
The solid modelling of the aircraft wing is
made using CAD tool CATIA V5 R19 to develop
the solid model of the wing. The modelling of the
aircraft wing structure is explained in the following
steps.
I. Generation of the airfoils at the root and tip using
the NACA profiles.
1. Plot the points calculated from the NACA profile
standards [9]. Plot the points using the option: Points
using co-ordinates
As per NACA 63-215
(Stations and ordinates given
in per cent of airfoil chord)
Upper Surface Lower Surface
Station Ordinate Station Ordinate
0 0 0 0
0.5 1.3786 0.5 -1.0398
0.75 1.6465 0.75 -1.2927
1.25 2.0754 1.25 -1.6759
2.5 2.8678 2.5 -2.3445
5 4.0291 5 -3.276
7.5 4.9045 7.5 -3.9589
10 5.6134 10 -4.4985
15 6.7137 15 -5.3147
20 7.5079 20 -5.8818
25 8.0583 25 -6.2502
30 8.3985 30 -6.4471
35 8.5297 35 -6.4694
40 8.4553 40 -6.3169
45 8.1924 45 -6.0053
50 7.7672 50 -5.5608
55 7.2048 55 -5.0096
60 6.529 60 -4.3769
65 5.7571 65 -3.682
70 4.9129 70 -2.9514
75 4.0219 75 -2.2141
80 3.1123 80 -1.5033
85 2.2185 85 -0.8605
90 1.3741 90 -0.3318
95 0.6202 95 0.0143
100 0 100 0
L.E. radius = 1.473 percent c
slope of mean line at LE = 0.0842
As per NACA 64-412
(Stations and ordinates given
in per cent of airfoil chord)
Upper Surface Lower Surface
Station Ordinate Station Ordinate
0 0 0 0
0.5 1.241 0.5 -0.7391
0.75 1.4656 0.75 -0.92
1.25 1.8291 1.25 -1.1787
2.5 2.5053 2.5 -1.5879
5 3.5203 5 -2.1181
7.5 4.3059 7.5 -2.4974
10 4.9575 10 -2.794
15 6.0007 15 -3.2444
20 6.7896 20 -3.5607
25 7.3781 25 -3.7724
30 7.7909 30 -3.8892
35 8.0426 35 -3.9174
40 8.1165 40 -3.8348
45 7.9859 45 -3.6088
50 7.6851 50 -3.2724
55 7.248 55 -2.8612
60 6.6952 60 -2.3979
65 6.0431 65 -1.9025
70 5.3061 70 -1.394
75 4.4979 75 -0.8929
80 3.6355 80 -0.4262
85 2.7387 85 -0.0286
90 1.829 90 0.2528
95 0.9238 95 0.3444
100 0 100 0
L.E. radius = 1.004 percent c
slope of mean line at LE = 0.1685
2. Create the splines making the top and bottom part
of the aerofoil. Leave the leading edge point to give
the leading edge radius.
4. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 4 | P a g e
Fig.3: Upper and Lower surface splines of NACA 63-
215
Fig.4: Upper and Lower surface splines of NACA 64-
412
3. Generation of wing surface using the aerofoil profiles
at the root and the tip.
Fig.5: Master Geometry (Wing Surface) of Mooney
M20TN Acclaim Aircraft Wing
The master geometry of Mooney M20TN
Acclaim Aircraft Wing is shown in Fig.5. This is the
CAD model which is considered for carrying out CFD
analysis to find out the pressure distribution. This data is
vital in carrying out structural analysis and then pre-
stressed modal analysis for the study of vibration
characteristics of the wing.
IV. RESULTS AND DISCUSSIONS
Aerodynamic complications in general are
often difficult to solve by analytical methods.
Experimental or numerical simulation can be used to
analyze these computational prototypes. To solve
aerodynamic problems experimentally heavy cost are
involved; hence the numerical method is more preferred.
This work furnishes the modeling and simulating
procedure of computational fluid dynamic (CFD)
problem on an aircraft wing model, using root airfoil
section as NACA 63-215 and tip airfoil section as NACA
64-412. Pressure and velocity distribution on the surface
of an aircraft wing is analyzed using ANSYS Fluent.
The fluid flow is considered as airflow. The
flow properties are chosen to be similar to that used in
the experiment, such as the density is 1.225kg/m3, and
the kinematics viscosity is 1.7894e-5. All parameters of
the above materials are applied to set for simulations.
In order to achieve more accurate results, a
bottom up approach method has been adopted in the
design. In bottom up approach the wing is first modeled
without internal structural member (i.e. spars, ribs etc.)
and then analyzed to arrive aerodynamic pressure loads.
ANSYS Fluent is able to provide several
graphic and animation types, such as pressure and
velocity distributions etc.
Fig.6 and fig.7 shows pressure distribution
contours in the airflow, when the velocity applied at the
inlet is 122m/s (438km/h). As can be noticed, the high-
pressure regions appear at the leading edge and on the
lower surface of airfoil. The low pressure region appears
on the upper surface of the airfoil. This analysis is
accurate with the theory of lift generation.
Fig.6: Pressure Distribution at the wing root
Fig.7: Pressure Distribution at the wing tip.
5. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 5 | P a g e
Velocity is also an important property to be
studied in the airflow over the airfoil section. Pressure is
inversely proportional to velocity.
Fig.8: Velocity Distribution at the wing root.
Fig.9: Velocity Distribution at the mid span of the
wing.
Fig.10: Velocity Distribution at the wing tip
Fig.8 to Fig.10 shows velocity distribution
contours in the airflow, when the velocity applied at the
inlet is 122m/s (438km/h). As can be noticed, the high-
velocity regions appear on the upper surface of airfoil.
The low velocity region appears on the lower surface of
the airfoil. This analysis is accurate with the theory of lift
generation.
V. STRUCTURAL ANALYSIS OF
AIRCRAFT WING
In this project detailed design of aircraft wing
using NACA standards is made by using CATIA V5
R19. Stress analysis of the wing is carried out to compute
the stresses, deformation and strains at aircraft wing
structure. Finite Element Approach is applied for finding
stresses using ANSYS workbench 14.5. Pressure loads
are applied on the wing to carry out structural analysis.
Fig.11: Total deformation in wing
Fig.12: Equivalent (von-Mises) stress in wing
Fig.13: Maximum principal stress in wing
6. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 6 | P a g e
Fig.14: Equivalent strain in wing
Fig.12 shows the Equivalent tensile stress or
von-Mises stress. It states that the material starts to yield
when the von-Mises stress reaches a critical value, yield
strength. Uniform stress distribution is observed all over
the wing but maximum stress is developed close to the
root section of wing. In this case, the von-Mises stress
observed in the wing analysis is 231.62 Mpa which is
lower than the yield strength of the aluminium alloy. Fig.
13 shows maximum principal stress distribution of the
wing under pressure load. The maximum principal stress
noticed in the structure is 175.66 Mpa which is lower
than the yield strength of the material. The structure is
safe because the stress magnitude which is obtained from
the analysis is less than the yield strength of the
structural material. Deflection of the wing is shown in
Fig.11, the wing bends upwards because of pressure
load.
VI. PRE-STRESSED MODAL
ANALYSIS
Dynamic properties of aircraft wing structure
can be studied by modal analysis under vibration
excitation. In aircraft wing vibration occurs due to the lift
load and the load due to mounting engine on the wing.
The modal analysis uses the overall mass and stiffness
property of the structure to find the various periods at
which it will naturally resonate. Dynamic analysis
comprised of deformation calculations due to inertial
loads at higher load factors and estimation of natural
frequencies and mode shapes. The mode shapes,
deformation and corresponding frequencies are shown in
figures from 15 to 24 and table 1.
Fig.15: Wing deformation at mode 1
Fig.16: Wing deformation at mode 2
Fig.17: Wing deformation at mode 3
Fig.18: Wing deformation at mode 4
Fig.19: Wing deformation at mode 5
7. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 7 | P a g e
Fig.20: Wing deformation at mode 6
Fig.21: Wing deformation at mode 7
Fig.22: Wing deformation at mode 8
Fig. 23: Wing deformation at mode 9
Fig. 24: Wing deformation at mode 10
Table 1: Natural Frequency, Max Deformation and
Mode shapes
Mode No. Frequency (Hz)
Max. Deformation
(mm)
1 10.352 11.383
2 37.096 12.564
3 57.462 11.034
4 66.974 11.936
5 78.221 12.992
6 125.7 13.099
7 136.68 12.176
8 143.33 14.704
9 179.65 17.164
10 198 15.494
VII. CONCLUSIONS AND SCOPE FOR
FUTURE WORK
The use of computer aided engineering
procedures to model, analyze and optimize proves to be
the most economic, reliable, and faster and user friendly
method to be adopted by the researchers and the
engineers to cope up the industry requirements for design
changes. The Computer Aided Design Tools and NACA
standards have been accomplished to design the wing
structure. The vibration characteristics of the wing
structures are studied by modal analysis to find the
natural frequency of the wing structures.
The CFD results revealed that the pressure on
the upper surface of the wing for all the wing section
planes (butt planes-BL) is less, about -4.97e3N/mm2, as
compared to the pressure on the lower surface, about
1.08e4 N/mm2, which satisfy the theory of lift
generation. The pre-stressed modal analysis shows the
correlation of the stress, deformation and the
corresponding mode of vibration. It is found that the
maximum deformation of 17.164 mm is corresponding
to the modal frequency of 179.65 Hz which can be
considered as design frequency of the wing structure.
However the fundamental natural frequency of the wing
structure is 10.352 Hz for the deformation of 11.383 mm.
The future scope of the research would be the
simulation of the wing in the design phase itself by using
this method. The Noise, Vibration and Harshness (NVH)
studies can give an insight for the design of the aircraft
wing for sturdy and stable structure. The aircraft wing
8. Nataraj Kuntoji. Int. Journal of Engineering Research and Application www.ijera.com
ISSN : 2248-9622, Vol. 7, Issue 4, ( Part -4) April 2017, pp.01-08
www.ijera.com DOI: 10.9790/9622-0704040108 8 | P a g e
design can be modified or optimized by using this
method would lead to a new method to incorporate the
NVH problems in aircraft design using CAE approach.
REFERENCES
[1]. http://www.allstar.fiu.edu/aero/flight12.htm
[2]. https://en.wikipedia.org/wiki/Mooney_M20
[3]. E.N. Jacobs, K.E. Ward, & R.M.
Pinkerton. NACA Report No. 460, "The
characteristics of 78 related airfoil sections
from tests in the variable-density wind tunnel".
NACA, 1933.
[4]. Nguyen Minh Triet, Nguyen Ngoc Viet, and
Pham Manh Thang “Aerodynamic Analysis of
Aircraft Wing” VNU Journal of Science:
Mathematics – Physics, Vol. 31, No. 2 (2015)
68-75.
[5]. Kakumani Sureka and R Satya Meher
“Modeling and Structural Analysis on A300
Flight Wing by using ANSYS” International
Journal of Mechanical Engineering and
Robotics Research Vol. 4, No. 2, April 2015.
[6]. Sudhir Reddy Konayapalli and Y Sujatha
“Design and Analysis of Aircraft Wing”
International Journal and Magazine of
Engineering, Technology, Management and
Research. Volume No: 2 (2015), Issue No: 9
(September).
[7]. Lica Flore and Albert Arnau Cubillo “
Dynamic Mechanical Analysis of an Aircraft
Wing with emphasis on vibration modes
change with loading” International Conference
of Scientific Paper AFASES 2015 Brasov, 28-
30 May 2015.
[8]. Farrukh Mazhar and Abdul Munem Khan “
Structural Design of a UAV Wing using Finite
Element Method” 51st
AIAA/ASME/ASCE/AHS/ASC Structures,
Structural Dynamics, and Materials
Conference<BR>18th 12 - 15 April 2010,
Orlando, Florida.
[9]. http://www.pdas.com/sections6.html