NASA and its industry partners are investigating a blended wing aircraft concept for potential use as a future air transport for both civilian and military applications. https://www.nasa.gov/centers/langley/news/factsheets/FS-2003-11-81-LaRC.html
CFD Studies of Blended Wing Body Configuration for High Angles of Attack -- Z...Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
Blended Wing Body (BWB) configurations offer a unique advantage of generating lift from the fuselage. The research paper aims to study several configurations aerodynamically for the viability of use in actual flight. The code is validated using the configuration from UiTM Malaysia. Simulations are performed at high angles of attack ranging from 20 deg to 40 deg. Good agreement is seen in RANS CFD and low speed wind tunnel data. The comparison gives confidence that BWB can be simulated at high angles of attack. Authors - Irshad Khan and Deepak Patil (Zeus Numerix), DN Santhosh (SDM CoE)
A Blended Wing Body (BWB) aircraft is a configuration where the wing and fuselage are integrated which essentially results in a large flying wing. BWB aircraft were previously called ‘tailless airplanes’ and ‘Flying-Wing aircraft’. The BWB configuration has shown promise in terms of aerodynamic efficiency, in particular for very large transport aircraft, because the configuration has a single lifting surface that means an aerodynamically clean configuration.
In recent years, air transportation has increased between major cities. Conventional aircraft's lack fuel efficiency, high Lift to Drag (L/D) ratio, high payload carrying capacity since there has not been a major technological breakthrough in aerodynamic geometry. Hence, there has been a need to develop a new composite structure to push the boundaries of current technologies and to breathe new life into civil transportation. Blended Wing Body (BWB) bridges the gap between future requirements. The BWB configuration is a new concept in aircraft design which provides greater internal volume, aerodynamics and structural efficiency, noise reduction, and most importantly significant improvement on cost-per-seat-mile. The design approach of BWB is to maximize overall efficiency by integrating the propulsion systems, wings, and the body into a single lifting surface. BWB is a unique tailless single entity where the fuselage is merged with wing and tail. Blended wing body has flattened and airfoil surface which contributes higher lift than conventional ones. The objective of this paper is to study aerodynamic study of blended wing body layout.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
This document discusses the development of a blended wing micro air vehicle (MAV). It begins by defining MAVs and blended wing body aircraft. It then outlines the advantages of blended wing design, such as higher lift-to-drag ratio and lower fuel consumption. The document proceeds to describe the steps taken to develop the blended wing MAV, including aerodynamic studies to select optimal airfoils and planform shape, as well as designing for stability with vertical wings and winglets. It concludes by discussing the production of the airframe and skin and final assembly and testing of the blended wing MAV model.
The presentation was prepared for an Technical Paper Presentation competition. It contains basic conceptual explanations pertaining to the BWB concept.
The document discusses the design and CFD analysis of a blended wing body (BWB) unmanned aerial vehicle (UAV) with high lift devices. It provides background on the BWB concept, which merges the fuselage and wing into a single lifting body to improve aerodynamic efficiency. The project involves designing a BWB UAV using CATIA, meshing it in ANSYS, and performing CFD analysis in ANSYS CFX to analyze aerodynamic forces and flow patterns with and without high lift devices at different angles of attack. The results are compared to study the effects of the high lift devices on lift, drag and stall angle.
CFD Studies of Blended Wing Body Configuration for High Angles of Attack -- Z...Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
Blended Wing Body (BWB) configurations offer a unique advantage of generating lift from the fuselage. The research paper aims to study several configurations aerodynamically for the viability of use in actual flight. The code is validated using the configuration from UiTM Malaysia. Simulations are performed at high angles of attack ranging from 20 deg to 40 deg. Good agreement is seen in RANS CFD and low speed wind tunnel data. The comparison gives confidence that BWB can be simulated at high angles of attack. Authors - Irshad Khan and Deepak Patil (Zeus Numerix), DN Santhosh (SDM CoE)
A Blended Wing Body (BWB) aircraft is a configuration where the wing and fuselage are integrated which essentially results in a large flying wing. BWB aircraft were previously called ‘tailless airplanes’ and ‘Flying-Wing aircraft’. The BWB configuration has shown promise in terms of aerodynamic efficiency, in particular for very large transport aircraft, because the configuration has a single lifting surface that means an aerodynamically clean configuration.
In recent years, air transportation has increased between major cities. Conventional aircraft's lack fuel efficiency, high Lift to Drag (L/D) ratio, high payload carrying capacity since there has not been a major technological breakthrough in aerodynamic geometry. Hence, there has been a need to develop a new composite structure to push the boundaries of current technologies and to breathe new life into civil transportation. Blended Wing Body (BWB) bridges the gap between future requirements. The BWB configuration is a new concept in aircraft design which provides greater internal volume, aerodynamics and structural efficiency, noise reduction, and most importantly significant improvement on cost-per-seat-mile. The design approach of BWB is to maximize overall efficiency by integrating the propulsion systems, wings, and the body into a single lifting surface. BWB is a unique tailless single entity where the fuselage is merged with wing and tail. Blended wing body has flattened and airfoil surface which contributes higher lift than conventional ones. The objective of this paper is to study aerodynamic study of blended wing body layout.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
This document discusses the development of a blended wing micro air vehicle (MAV). It begins by defining MAVs and blended wing body aircraft. It then outlines the advantages of blended wing design, such as higher lift-to-drag ratio and lower fuel consumption. The document proceeds to describe the steps taken to develop the blended wing MAV, including aerodynamic studies to select optimal airfoils and planform shape, as well as designing for stability with vertical wings and winglets. It concludes by discussing the production of the airframe and skin and final assembly and testing of the blended wing MAV model.
The presentation was prepared for an Technical Paper Presentation competition. It contains basic conceptual explanations pertaining to the BWB concept.
The document discusses the design and CFD analysis of a blended wing body (BWB) unmanned aerial vehicle (UAV) with high lift devices. It provides background on the BWB concept, which merges the fuselage and wing into a single lifting body to improve aerodynamic efficiency. The project involves designing a BWB UAV using CATIA, meshing it in ANSYS, and performing CFD analysis in ANSYS CFX to analyze aerodynamic forces and flow patterns with and without high lift devices at different angles of attack. The results are compared to study the effects of the high lift devices on lift, drag and stall angle.
The document summarizes a graduate student project to design and build a blended wing body aircraft called Hyperion that investigates green aircraft technologies. The project aims to reduce noise, fuel consumption, and emissions. Key aspects include a hybrid gas-electric propulsion system, autonomous flight capabilities using an autopilot, and manufacturing composite wing structures using carbon fiber. Testing will involve building half-scale prototypes and conducting flight tests to prove the aerodynamic design.
Incorporation Of Shape Memory Alloy Actuators Into Morphing Aerostructures - IIAvillager_learns_computer
The document discusses applications of shape memory alloys (SMAs) in aerospace structures, specifically fixed-wing aircraft, rotorcraft, and spacecraft. It notes that SMAs are being used for both novel morphing designs and replacements for conventional actuators due to their compact size, power, and simplicity. For fixed-wing aircraft, examples of local actuation using SMAs include tabs, flaps, and engine inlets/nozzles, where SMA components can eliminate hinges or permit actuation in small spaces. The document provides an overview of current and potential uses of SMA morphing technologies in aerospace vehicles.
This document provides details of an aircraft design project for a new personal jet called "The Flash" being designed by Kent Aerospace. It includes sections on requirements analysis, technical design, manufacturing plan, regulatory compliance, program management, finance, marketing, and socioeconomic impacts. The technical design section provides details on sizing methodology, assumptions, wing and tail geometry, thrust-to-weight ratio, powerplant specifications, wing loading data, and performance results. The design utilizes twin DGEN 380 turbofan engines from Price Induction and is intended to carry 3 passengers up to 800 nautical miles at a cruise speed of 230 knots.
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.
This document summarizes a student aircraft design project to design a cargo plane. The objectives are to design a cargo plane to carry 600,000 kg over 4,000 km with a cruise speed of 850 km/h. The preliminary design was completed and included collecting comparative data, selecting parameters, estimating weights, selecting engines and airfoils, and creating a wing layout. Structural analysis was performed on the wing and fuselage.
Design your flight 2013 guru gobind singh indraprastha university-team leo (2)Ishmeet Sachdeva
The document summarizes the design process for an aircraft. It describes how various design options were analyzed using software before selecting a monoplane design with a NACA 2417 airfoil made of balsa wood. Prototypes were constructed and tested before the final manufacturing process. Electrical components like motors and batteries were chosen based on calculations. Diagrams show the aircraft design, manufacturing steps, and analysis of components like the wings and landing gear to ensure the design meets requirements.
This document summarizes the design of the Jayhawk Economic Turboprop Transport (J.E.T.T.) aircraft for the 2013-2014 AIAA Undergraduate Team Aircraft Design Competition. It provides the mission specifications for a new regional turboprop airliner, including a 400 nautical mile economic mission carrying 75 passengers and a 1,600 nautical mile design mission carrying 67 passengers. It then describes the initial configurations considered and presents analysis on determining design parameters through statistical modeling techniques. Key aspects of the preliminary aircraft design are summarized, including engine selection, wing design, and layout of major systems.
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.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
This document 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.
This document discusses the structural design and analysis of an 8-seater short range business jet aircraft. It begins with an introduction to the project and overview of structural design. It then presents the V-n diagram, which establishes the flight envelope and maneuvering limits of the aircraft based on its load factor ratings. The majority of the document focuses on analyzing and designing the structural components of the wings and fuselage through methods like load estimation, shear force and bending moment distribution, material selection, and sizing of spars, stringers and other members. Design considerations are also discussed for miscellaneous wing components like the fuel tank, ribs and empennage. Graphs and diagrams are included to illustrate the structural analysis.
The document outlines a research project to design and test advanced wing structures for unmanned aerial vehicles that are lighter yet able to withstand greater loads. Various wing design options and materials will be considered and prototypes will be manufactured and tested to evaluate their strength, weight, production cost, and feasibility. The goals are to develop a wing design that meets criteria for the annual AIAA Student Design Build Fly competition and can be modified for future competitive aircraft designs.
This document describes the design of a fighter aircraft. It discusses the conceptual design phase where the overall shape, size, weight and performance are determined. Comparative studies are conducted on different types of airplanes to select the appropriate configuration. Key parameters like wing type, engine selection and aerodynamic surfaces are analyzed and optimized. Performance calculations are carried out to evaluate the design. Three views and design specifications of the final fighter aircraft are presented.
The document presents the design of the LAT-1 large air tanker aircraft by Ember Aviation in response to the 2015-2016 AIAA Foundation Undergraduate Team Aircraft Design Competition. The LAT-1 is designed to carry 5,000 gallons of water or retardant with a maximum weight of 45,000 lbs and perform 3 drops per sortie within a 200 nm radius of the base, as well as have a ferry range of 2,500 nm. The LAT-1 features a retardant tank fuselage shape with two engines mounted on top of the wings. Ember Aviation's goal was to eliminate wasted space on the aircraft by integrating all components, such as the cockpit and payload tank, directly into the aircraft structure
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
The document describes a personal jet aircraft called the Recurve designed by students. The Recurve is intended to make private aircraft ownership more affordable and can carry a pilot and two passengers. It has a range of over 1,000 miles, can cruise at over 190 mph at 20,000 feet, and can takeoff and land on runways under 2,000 feet. The students selected a canard configuration for its suitability to amateur pilots while providing space for passengers.
This document provides an overview of the aircraft design process for a military training aircraft. It includes collecting reference data, preliminary sizing calculations to determine the empty weight, wing area and aspect ratio. Further iterations were needed to achieve stability. Performance analysis was conducted including drag and thrust curves. Cost estimates were also outlined. The design process involved collecting data, iterative sizing, aerodynamic analysis and stability evaluation. Students were assigned homework to present their work in a 30 minute presentation.
This document describes a study analyzing the impact of cruise speed on the structural weight of the wings for a commercial twinjet aircraft. Ten wing designs were generated with varying cruise Mach numbers from 0.75 to 0.9 using a preliminary design tool called Asa Turbo. The wing designs were then modeled in CATIA and their structural weights estimated more accurately using a tool called PDWSW that performs preliminary wing structural design. PDWSW optimizes the wing structure layout and sizing to minimize weight while meeting strength requirements. The results provide guidance on selecting an optimal cruise speed by showing how wing structural weight evolves with speed for the aircraft concept studied.
International Journal of Engineering Research and Development IJERD Editor
• Electrical, Electronics and Computer Engineering,
• Information Engineering and Technology,
• Mechanical, Industrial and Manufacturing Engineering,
• Automation and Mechatronics Engineering,
• Material and Chemical Engineering,
• Civil and Architecture Engineering,
• Biotechnology and Bio Engineering,
• Environmental Engineering,
• Petroleum and Mining Engineering,
• Marine and Agriculture engineering,
• Aerospace Engineering.
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
Design and Fabrication of Blended Wing Bodyvivatechijri
This document describes the design and fabrication of a blended wing body (BWB) unmanned aerial vehicle. It discusses the BWB concept and its advantages over conventional aircraft designs, including greater internal space and aerodynamic efficiency. The authors designed a BWB model made of balsa and basswood with airfoils selected for lift generation. Analysis and fabrication steps are outlined, including material selection, airfoil choice, configuration design, lift calculation using both theoretical and computational fluid dynamics methods, and manufacturing of individual parts and final assembly. The conclusions state that the designed BWB provides higher payload capacity and volume than conventional designs while enhancing the authors' technical skills.
The document summarizes a graduate student project to design and build a blended wing body aircraft called Hyperion that investigates green aircraft technologies. The project aims to reduce noise, fuel consumption, and emissions. Key aspects include a hybrid gas-electric propulsion system, autonomous flight capabilities using an autopilot, and manufacturing composite wing structures using carbon fiber. Testing will involve building half-scale prototypes and conducting flight tests to prove the aerodynamic design.
Incorporation Of Shape Memory Alloy Actuators Into Morphing Aerostructures - IIAvillager_learns_computer
The document discusses applications of shape memory alloys (SMAs) in aerospace structures, specifically fixed-wing aircraft, rotorcraft, and spacecraft. It notes that SMAs are being used for both novel morphing designs and replacements for conventional actuators due to their compact size, power, and simplicity. For fixed-wing aircraft, examples of local actuation using SMAs include tabs, flaps, and engine inlets/nozzles, where SMA components can eliminate hinges or permit actuation in small spaces. The document provides an overview of current and potential uses of SMA morphing technologies in aerospace vehicles.
This document provides details of an aircraft design project for a new personal jet called "The Flash" being designed by Kent Aerospace. It includes sections on requirements analysis, technical design, manufacturing plan, regulatory compliance, program management, finance, marketing, and socioeconomic impacts. The technical design section provides details on sizing methodology, assumptions, wing and tail geometry, thrust-to-weight ratio, powerplant specifications, wing loading data, and performance results. The design utilizes twin DGEN 380 turbofan engines from Price Induction and is intended to carry 3 passengers up to 800 nautical miles at a cruise speed of 230 knots.
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.
This document summarizes a student aircraft design project to design a cargo plane. The objectives are to design a cargo plane to carry 600,000 kg over 4,000 km with a cruise speed of 850 km/h. The preliminary design was completed and included collecting comparative data, selecting parameters, estimating weights, selecting engines and airfoils, and creating a wing layout. Structural analysis was performed on the wing and fuselage.
Design your flight 2013 guru gobind singh indraprastha university-team leo (2)Ishmeet Sachdeva
The document summarizes the design process for an aircraft. It describes how various design options were analyzed using software before selecting a monoplane design with a NACA 2417 airfoil made of balsa wood. Prototypes were constructed and tested before the final manufacturing process. Electrical components like motors and batteries were chosen based on calculations. Diagrams show the aircraft design, manufacturing steps, and analysis of components like the wings and landing gear to ensure the design meets requirements.
This document summarizes the design of the Jayhawk Economic Turboprop Transport (J.E.T.T.) aircraft for the 2013-2014 AIAA Undergraduate Team Aircraft Design Competition. It provides the mission specifications for a new regional turboprop airliner, including a 400 nautical mile economic mission carrying 75 passengers and a 1,600 nautical mile design mission carrying 67 passengers. It then describes the initial configurations considered and presents analysis on determining design parameters through statistical modeling techniques. Key aspects of the preliminary aircraft design are summarized, including engine selection, wing design, and layout of major systems.
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.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
This document 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.
This document discusses the structural design and analysis of an 8-seater short range business jet aircraft. It begins with an introduction to the project and overview of structural design. It then presents the V-n diagram, which establishes the flight envelope and maneuvering limits of the aircraft based on its load factor ratings. The majority of the document focuses on analyzing and designing the structural components of the wings and fuselage through methods like load estimation, shear force and bending moment distribution, material selection, and sizing of spars, stringers and other members. Design considerations are also discussed for miscellaneous wing components like the fuel tank, ribs and empennage. Graphs and diagrams are included to illustrate the structural analysis.
The document outlines a research project to design and test advanced wing structures for unmanned aerial vehicles that are lighter yet able to withstand greater loads. Various wing design options and materials will be considered and prototypes will be manufactured and tested to evaluate their strength, weight, production cost, and feasibility. The goals are to develop a wing design that meets criteria for the annual AIAA Student Design Build Fly competition and can be modified for future competitive aircraft designs.
This document describes the design of a fighter aircraft. It discusses the conceptual design phase where the overall shape, size, weight and performance are determined. Comparative studies are conducted on different types of airplanes to select the appropriate configuration. Key parameters like wing type, engine selection and aerodynamic surfaces are analyzed and optimized. Performance calculations are carried out to evaluate the design. Three views and design specifications of the final fighter aircraft are presented.
The document presents the design of the LAT-1 large air tanker aircraft by Ember Aviation in response to the 2015-2016 AIAA Foundation Undergraduate Team Aircraft Design Competition. The LAT-1 is designed to carry 5,000 gallons of water or retardant with a maximum weight of 45,000 lbs and perform 3 drops per sortie within a 200 nm radius of the base, as well as have a ferry range of 2,500 nm. The LAT-1 features a retardant tank fuselage shape with two engines mounted on top of the wings. Ember Aviation's goal was to eliminate wasted space on the aircraft by integrating all components, such as the cockpit and payload tank, directly into the aircraft structure
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
The document describes a personal jet aircraft called the Recurve designed by students. The Recurve is intended to make private aircraft ownership more affordable and can carry a pilot and two passengers. It has a range of over 1,000 miles, can cruise at over 190 mph at 20,000 feet, and can takeoff and land on runways under 2,000 feet. The students selected a canard configuration for its suitability to amateur pilots while providing space for passengers.
This document provides an overview of the aircraft design process for a military training aircraft. It includes collecting reference data, preliminary sizing calculations to determine the empty weight, wing area and aspect ratio. Further iterations were needed to achieve stability. Performance analysis was conducted including drag and thrust curves. Cost estimates were also outlined. The design process involved collecting data, iterative sizing, aerodynamic analysis and stability evaluation. Students were assigned homework to present their work in a 30 minute presentation.
This document describes a study analyzing the impact of cruise speed on the structural weight of the wings for a commercial twinjet aircraft. Ten wing designs were generated with varying cruise Mach numbers from 0.75 to 0.9 using a preliminary design tool called Asa Turbo. The wing designs were then modeled in CATIA and their structural weights estimated more accurately using a tool called PDWSW that performs preliminary wing structural design. PDWSW optimizes the wing structure layout and sizing to minimize weight while meeting strength requirements. The results provide guidance on selecting an optimal cruise speed by showing how wing structural weight evolves with speed for the aircraft concept studied.
International Journal of Engineering Research and Development IJERD Editor
• Electrical, Electronics and Computer Engineering,
• Information Engineering and Technology,
• Mechanical, Industrial and Manufacturing Engineering,
• Automation and Mechatronics Engineering,
• Material and Chemical Engineering,
• Civil and Architecture Engineering,
• Biotechnology and Bio Engineering,
• Environmental Engineering,
• Petroleum and Mining Engineering,
• Marine and Agriculture engineering,
• Aerospace Engineering.
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
Design and Fabrication of Blended Wing Bodyvivatechijri
This document describes the design and fabrication of a blended wing body (BWB) unmanned aerial vehicle. It discusses the BWB concept and its advantages over conventional aircraft designs, including greater internal space and aerodynamic efficiency. The authors designed a BWB model made of balsa and basswood with airfoils selected for lift generation. Analysis and fabrication steps are outlined, including material selection, airfoil choice, configuration design, lift calculation using both theoretical and computational fluid dynamics methods, and manufacturing of individual parts and final assembly. The conclusions state that the designed BWB provides higher payload capacity and volume than conventional designs while enhancing the authors' technical skills.
The document summarizes the accomplishments of the GlobalFlyer aircraft, designed by Scaled Composites to set the record for fastest non-stop circumnavigation of the Earth in 67 hours. Key aspects included its composite construction, 114-foot wingspan, 44-foot length, and ability to carry over 18,000 pounds of fuel distributed throughout wing and pod tanks. While a unique design, no other manufacturers have fully replicated its approach, and its single occupant limits commercial applications. However, the composite technologies could eventually help solve future high-efficiency aviation needs.
Proceedings of the institution of mechanical engineers, part g journal of ae...Spectre Industries, LLC
This document presents a method for predicting the mass of a blended wing body (BWB) airframe. The method uses a theoretically-based approach modified with empirical data from other aircraft. It treats the airframe mass primarily as a wing mass problem, with penalties added to account for using part of the wing as a payload volume. The method was applied to several BWB design studies and provided reasonably accurate mass predictions, though it cannot be fully validated since no full-size BWB aircraft have been built and flown.
This is my first crack at writing a technical report for an assignment in a mechanical engineering course at the University of Alberta. How was the clarity? Any feedback on how I can improve?
First developed a few decades ago, the Blended Wing Body or BWB is a hybrid aircraft design that makes a plane look like a manta ray. https://scottbealeaviation.wordpress.com/2018/06/28/is-the-blended-wing-body-the-future-of-aircraft-design/
This is the statement of work for my Advanced Technology Demonstration Aircraft project, to inspire interest in aerospace engineering for the RAeS and AIAA.
This document discusses the use of computational modeling to study hydrofoil design improvements for reducing water takeoff distances of amphibious aircraft. It provides background on challenges in amphibious aircraft design and limited prior research on using hydrofoils. The author develops a preliminary computational framework to assess hydrofoil performance and effectiveness for amphibious aircraft applications, focusing on optimizing hydrofoil position, span, and incidence angle to minimize water takeoff distance while maintaining aircraft stability. A case study applies this framework to a 10-seater amphibious aircraft concept, finding that a hydrofoil can reduce hull resistance and water takeoff distance.
Rapid Development of a Rotorcraft UAV System - AHS Tech Specialists Meeting 2005Mark Hardesty
This document summarizes the development of a rotorcraft unmanned aerial vehicle (UAV) system by Boeing Phantom Works over less than one year. They selected the MD 530F helicopter due to its performance capabilities and military counterpart. The design integrated commercial off-the-shelf hardware and proprietary Boeing flight control software. Bench and flight testing were prioritized to rapidly expand the flight envelope from initial engagement of the electrical flight controls to autonomous takeoffs, landings and navigation. The manual override capability allowed high-risk prototype systems to be safely tested.
An Economic Analysis of the Viability of a Supersonic Business JetMichael Lopez
This document presents an economic analysis of potential supersonic business jet designs. Systems engineering tools such as an affinity diagram, tree diagram, prioritization matrix, quality function development, and TOPSIS analysis were used to evaluate designs. It was determined that with current technology, a supersonic business jet would not be more profitable than subsonic business jet options like the Cessna Citation X. Therefore, a supersonic business jet would not be economically viable at this time.
The document describes the development of a wireless cut-down system for high altitude balloons (HABs) conducted by Brendan Batliner and Milan Shah at the Adler Planetarium. The system uses Arduino microcontrollers and XBee wireless transceivers to allow sensors on the HAB payload to communicate wirelessly and trigger a cut-down based on programmed conditions. Testing confirmed the low-power wireless system could reliably trigger a cut-down. A Kalman filter was also developed to increase sensor accuracy by reducing noise. The wireless, modular cut-down system allows for more efficient flight control and expansion to integrate additional sensors.
Design and Computational Fluid Dynamic Analysis of Spiroid Winglet to Study i...IRJET Journal
This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
ARIES NASA Langley S Airborne Research FacilityKimberly Pulley
NASA acquired a Boeing 757 aircraft in 1994 to replace its aging Boeing 737 aircraft and continue aeronautical research. The 757 has undergone extensive modifications to transform it into a flying laboratory called ARIES. It features a Flight Deck Research Station and Transport Research System. ARIES conducts research flights to improve aviation safety, efficiency and capacity. Some examples of research include testing GPS landings, synthetic vision systems, and closely spaced approaches.
Unmanned Little Bird Testing Approach - AHS Tech Specists Meeting Jan 2009Mark Hardesty
The document summarizes the Unmanned Little Bird (ULB) program approach. The ULB program leveraged an existing aircraft design, the MD 530F helicopter, to create a full-size unmanned aerial vehicle (UAV) for testing new technologies with minimal risk. The first ULB flight occurred in September 2004 and demonstrated fully autonomous flight six weeks later. Over 576 flight hours of testing have helped advance UAV subsystem development and operational concepts. The ULB approach of reusing an existing airframe provides a cost-effective way to develop and qualify new technologies for VTOL UAVs.
This paper addresses an optimization of Unmanned Aerial Vehicle (UAV) flight trajectories
by bank-turn mechanism for a fixed-wing UAV at a constant altitude.
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.
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.
AIAA 2012 878 312 Hyperion Green AircraftJean Koster
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Blended Wing Body – A potential new aircraft design
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Blended Wing Body – A potential new aircraft design
NASA and its industry partners are investigating a blended wing aircraft concept for potential use as a future air transport for
both civilian and military applications. The concept is called the blended wing body (BWB). The BWB is a hybrid shape that
resembles a flying wing, but also incorporates features from conventional transport aircraft. This combination offers several
advantages over conventional tube-and wing airframes. The BWB airframe merges efficient high-lift wings with a wide airfoil-
shaped body, allowing the entire aircraft to generate lift and minimize drag. This shape helps to increase fuel economy and
creates larger payload (cargo or passenger) areas in the center body portion of the aircraft.
The basic concept for a blended wing body was first developed decades ago and variations of it have been used in the famous
B-2 bomber (a blended wing) and the lesser-known YB-49 (a pure flying wing from the 1940’s). Like the B-2, the BWB design
uses composite materials that are stronger and lighter than conventional metal construction. The BWB also has several control
surfaces on the trailing edge, like the B-2, instead of the conventional tail assembly.
Image above is artist concept of one version of the blended wing body aircraft.
The BWB shape allows unique interior designs. Cargo can be loaded or passengers can board from the front or rear of the
aircraft. The cargo or passenger area is distributed across the wide fuselage, providing a large usable volume. For passengers
2. in the interior of the craft, real-time video at every seat would take the place of window seats.
NASA and industry studies suggest that a large commercial BWB aircraft could be developed. Because of its efficient
configuration, the BWB would consume over 20 percent less fuel than a comparable conventional aircraft flying at high
subsonic cruise speeds over a 7,000 nautical-mile range. An aircraft of this type would have a wingspan slightly greater than a
Boeing 747 and could operate from existing airport terminals. The BWB would also weigh less, generate less noise and
emissions, and cost less to operate than an equally advanced conventional transport aircraft.
NASA BWB Research
NASA is studying the flying characteristics of the BWB. Because it is a configuration that has only been used in military
missions, there are a number of critical questions that researchers must address before a BWB can be commercially certified.
The primary goals of the research are to study the flight and handling characteristics of the BWB design, match the vehicle's
performance with engineering predictions based on computer and wind tunnel studies, develop and evaluate digital flight
controls, and assess the integration of the propulsion system to the airframe. Future research must also address the wide, flat
pressurized payload bay of the BWB.
Over the past several years, wind tunnel and freeflight model tests have been conducted to study particular aerodynamic
characteristics of the BWB design. At the NASA Langley Research Center in Hampton, Virginia, researchers tested five wind
tunnel models of three versions of the BWB to evaluate the concept's aerodynamic, noise, stability and control, and spin and
tumble characteristics. Data obtained during these tests were used to develop computer performance models and flight control
laws. The researchers will incorporate all wind tunnel (and later flight) data into simulations of a full-scale BWB to evaluate the
flying characteristics.
A scale model of an early blended wing body design was tested in one of the NASA Langley wind tunnels.
Research and Test Team
The NASA BWB Project is managed by Langley Research Center.
The BWB shape, called the outer mold line, was developed by The Boeing Phantom Works of Huntington Beach, California.
The Langley Full Scale Tunnel operated by Old Dominion University will be used for free-flight model tests of the BWB.
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