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.
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
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.
The document provides a design report for a micro class aircraft created by Team 310 of BMS College of Engineering for the SAE Aero Design West competition in 2015. The team designed a conventional aircraft configuration to maximize payload fraction and flight scores. Key aspects of the design included selecting a high lift airfoil, optimizing the wing and fuselage geometry, and utilizing lightweight composite and laser-cut materials. Performance was analyzed through finite element analysis, CFD, and wind tunnel testing. The manufacturing and testing process are also summarized.
1) The document describes the design of an aircraft using Cradle to Cradle principles, with the goal of making it at least 90% recyclable.
2) Key aspects of the design include using ethanol as a biofuel, an aluminum structure and thermoplastic composites for secondary structures, and a disassembly process that allows for almost full recycling.
3) Analysis shows the Cradle to Cradle design meets performance requirements while having a lower operating cost than comparable aircraft, demonstrating the viability of applying these principles in aircraft design.
The document is a design report for an aircraft called the L-406 Skycrane that was designed to compete in the Micro Class of the 2015 SAE Aero Design West competition. Some key points:
1) The aircraft was designed to have a maximum weight of 10 pounds and fit within a 6-inch diameter container in order to comply with competition rules. The goal was to achieve a high payload fraction of approximately 80%.
2) An innovative aspect of the design was that the entire aircraft was manufactured using additive manufacturing to reduce weight and accelerate the production process.
3) Performance analyses were conducted to determine that the aircraft could be hand-launched at 30 feet per second, complete two 180-degree
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.
The document provides details on the design of two aircraft, a Manufacturing Support Aircraft (MSA) and Production Aircraft (PA), for the 2015-2016 AIAA Design/Build/Fly competition. Key aspects of the design include:
- The PA is designed to have a single subassembly to maximize the competition score. It has a conventional high wing configuration.
- The MSA is designed in multiple sections to fit around and transport subassemblies of the PA.
- Both aircraft are designed to have minimal weight through efficient structures and use of composite materials, in order to maximize the competition score.
- Extensive testing was conducted involving 31 test flights to validate the design assumptions.
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 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
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.
The document provides a design report for a micro class aircraft created by Team 310 of BMS College of Engineering for the SAE Aero Design West competition in 2015. The team designed a conventional aircraft configuration to maximize payload fraction and flight scores. Key aspects of the design included selecting a high lift airfoil, optimizing the wing and fuselage geometry, and utilizing lightweight composite and laser-cut materials. Performance was analyzed through finite element analysis, CFD, and wind tunnel testing. The manufacturing and testing process are also summarized.
1) The document describes the design of an aircraft using Cradle to Cradle principles, with the goal of making it at least 90% recyclable.
2) Key aspects of the design include using ethanol as a biofuel, an aluminum structure and thermoplastic composites for secondary structures, and a disassembly process that allows for almost full recycling.
3) Analysis shows the Cradle to Cradle design meets performance requirements while having a lower operating cost than comparable aircraft, demonstrating the viability of applying these principles in aircraft design.
The document is a design report for an aircraft called the L-406 Skycrane that was designed to compete in the Micro Class of the 2015 SAE Aero Design West competition. Some key points:
1) The aircraft was designed to have a maximum weight of 10 pounds and fit within a 6-inch diameter container in order to comply with competition rules. The goal was to achieve a high payload fraction of approximately 80%.
2) An innovative aspect of the design was that the entire aircraft was manufactured using additive manufacturing to reduce weight and accelerate the production process.
3) Performance analyses were conducted to determine that the aircraft could be hand-launched at 30 feet per second, complete two 180-degree
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.
The document provides details on the design of two aircraft, a Manufacturing Support Aircraft (MSA) and Production Aircraft (PA), for the 2015-2016 AIAA Design/Build/Fly competition. Key aspects of the design include:
- The PA is designed to have a single subassembly to maximize the competition score. It has a conventional high wing configuration.
- The MSA is designed in multiple sections to fit around and transport subassemblies of the PA.
- Both aircraft are designed to have minimal weight through efficient structures and use of composite materials, in order to maximize the competition score.
- Extensive testing was conducted involving 31 test flights to validate the design assumptions.
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.
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.
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.
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.
This document provides a summary of the conceptual design process for a long range business jet. It begins with an analysis of the mission specifications and performance requirements. Next, it performs a comparative study of similar aircraft models to aid in the design. It then estimates the takeoff weight and analyzes wing loading and performance constraints. Subsequent chapters discuss the design of the main wing, fuselage, horizontal and vertical tails, propulsion system, takeoff and landing performance, lift devices, and structural and stability considerations. Detailed calculations and analyses are presented at each step to develop a completed aircraft design that meets all initial specifications.
The document provides information about rule changes for the 2016 SAE Aero Design competition, including new requirements for the Advanced Class. Major changes include allowing multiple payload drops per flight in Advanced Class, which will significantly impact aircraft center of gravity. Advanced Class aircraft must now prove they can successfully fly, drop a payload, and land before competing. The rules format has been rewritten for easier reading. Teams are advised to carefully read and understand all rules changes, as missing a change could prevent them from competing.
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.
The document provides an overview and design details for a next generation strategic military transport aircraft called the UR1T. Key points discussed include:
- The UR1T is designed to improve payload transportation capabilities and reduce loading/unloading times compared to the current fleet.
- Design aspects covered include the wing, engines, fuel system, payload integration, and flight envelope. Aerodynamic analyses were performed to determine wing and tail sizing.
- The UR1T is designed to carry a maximum payload of 300,000 lbs with a range of 1,800 nm at a cruise speed of Mach 0.75 and altitude of 30,000 ft.
- Payload integration focuses on fitting standard 463
The document summarizes the design of a fighter aircraft by Dudekula Jamal. It includes collecting reference data from 15 existing aircraft, estimating parameters like weight, selecting engines, designing the wing and tail, estimating lift and drag, and presenting performance characteristics. Diagrams and side views of the proposed design are also provided. The document concludes that the preliminary design addresses key considerations but that experience is important for successful aircraft design.
The document outlines the aircraft design process from initial requirements definition through detailed design, testing, and certification. It discusses establishing basic and general requirements, conducting feasibility studies, specifying detailed requirements, conceptual and preliminary design phases involving configuration selection, performance modeling, and optimization. Later phases include detailed design, ground and flight testing, and certification to clear the aircraft for intended operations. The process is iterative with frequent trade-offs and refinement of requirements and design.
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.
This document presents the final design review of an optimized sonic cruiser aircraft called the Aquila. It includes details on the aircraft layout and design, aerodynamic analysis, propulsion and performance calculations, stability and trim analysis. The aircraft is designed to carry 200 passengers with a maximum cruise speed of Mach 1 and an impressive range of over 7,600 nautical miles while cruising at altitudes above 40,000 feet. Tables and figures provide specifications, dimensions, and results of analyses on the aircraft's weight and balance, external geometry, lift and drag polars, thrust performance, static stability, and mission profiles.
1) The document outlines the iterative process of preliminary aircraft design for a military training aircraft.
2) Initial sizing used regression equations from historical data to estimate takeoff weight and wing loading.
3) Aerodynamic analysis revealed instability issues requiring design changes like increasing wing area.
4) Recalculating fuel requirements with more accuracy reduced weight and solved stability problems.
This document is a project report that analyzes and redesigns the landing gear of two light aircraft - the Piper PA28 and Grob G115. The report investigated landing gear failures using data from the Civil Aviation Authority. Finite element analysis was conducted on CAD models of the landing gears under different loading conditions. The results showed that three of the four original landing gears failed to meet safety standards. The report then redesigns the failing landing gears by changing materials and designs, and conducts new FEA to analyze if the redesigns meet standards.
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.
This document discusses subsonic flow analysis of a tailless aircraft using computational fluid dynamics (CFD). It begins with an introduction to tailless aircraft design and blended wing body (BWB) concepts. It then provides an overview of CFD, the software tools CATIA, Hypermesh, and Fluent that will be used in the analysis. The document outlines the methodology that will be followed, including designing the aircraft models in CATIA, meshing in Hypermesh, and performing CFD simulations and analysis in Fluent. It concludes that the results and discussion will provide comparisons of aerodynamic characteristics like lift, drag, pressure and velocity distributions between the tailless BWB design and a conventional aircraft design.
This document provides an overview of aircraft weight and balance processes. It defines key terms like center of gravity, moment, and maximum weights. It discusses how weight and balance must be managed on aircraft like the F-16 to ensure safety. The document demonstrates a weight and balance check on a Cessna 206 and uses iFly software to show a computational example on a Falcon 900EX. It emphasizes that operating within weight and balance limits is critical to flight safety.
To determine if a helicopter is within weight limits, a pilot must calculate the basic empty weight and consider the weight of the crew, passengers, cargo, fuel, and helicopter structure. The maximum gross weight and center of gravity range must also be checked to ensure structural integrity and safe handling. Improper loading that shifts the center of gravity outside the allowable range could cause stability and control issues. Accurate weight and balance calculations are important for safety.
This document describes the design process of a spheroid VTOL UAV. It outlines the objectives, which include designing a strong but lightweight structure within a budget of Rs 50,000. It also describes the flowchart process of designing, prototyping, testing, redesigning, manufacturing the final product, and final testing. The goals are to size the motor and propeller, integrate the flight control electronics, test and tune the flight control surfaces, and verify all objectives are met including withstanding impacts during landing.
Tutorial VSP Conference 2013, San Luis Obispo, CAHersh Amin
Vehicle Sketch Pad Structure Analysis Module (VSP SAM, http://vspsam.ae.utexas.edu/) tutorial presentation at the 2nd annual VSP (http://openvsp.org/) workshop held in San Luis Obispo, CA from Aug 7-9, 2013.
This document outlines a method for initial sizing of aircraft components. It discusses estimating the takeoff weight using statistical equations and iterating to a solution. It then describes determining the geometry of the fuselage, wing, tail surfaces, and control surfaces based on factors like the takeoff weight and engine location. Methods are provided for estimating weight fractions during different mission phases like takeoff, climb, cruise, and landing.
This document outlines the key considerations and tasks for a student design project on aircraft design. It discusses defining the problem and customers, assessing aircraft viability, understanding constraints, exploiting innovations, and organizing the design process. The document provides guidance on technical tasks like configuration selection, sizing, and drawings. It also addresses best practices for effective teamwork, such as managing meetings, assigning roles and responsibilities, and balancing individual strengths and weaknesses. The homework outlined is to summarize a textbook chapter, prepare a project plan and meeting templates, and define team member roles.
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.
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.
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.
This document provides a summary of the conceptual design process for a long range business jet. It begins with an analysis of the mission specifications and performance requirements. Next, it performs a comparative study of similar aircraft models to aid in the design. It then estimates the takeoff weight and analyzes wing loading and performance constraints. Subsequent chapters discuss the design of the main wing, fuselage, horizontal and vertical tails, propulsion system, takeoff and landing performance, lift devices, and structural and stability considerations. Detailed calculations and analyses are presented at each step to develop a completed aircraft design that meets all initial specifications.
The document provides information about rule changes for the 2016 SAE Aero Design competition, including new requirements for the Advanced Class. Major changes include allowing multiple payload drops per flight in Advanced Class, which will significantly impact aircraft center of gravity. Advanced Class aircraft must now prove they can successfully fly, drop a payload, and land before competing. The rules format has been rewritten for easier reading. Teams are advised to carefully read and understand all rules changes, as missing a change could prevent them from competing.
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.
The document provides an overview and design details for a next generation strategic military transport aircraft called the UR1T. Key points discussed include:
- The UR1T is designed to improve payload transportation capabilities and reduce loading/unloading times compared to the current fleet.
- Design aspects covered include the wing, engines, fuel system, payload integration, and flight envelope. Aerodynamic analyses were performed to determine wing and tail sizing.
- The UR1T is designed to carry a maximum payload of 300,000 lbs with a range of 1,800 nm at a cruise speed of Mach 0.75 and altitude of 30,000 ft.
- Payload integration focuses on fitting standard 463
The document summarizes the design of a fighter aircraft by Dudekula Jamal. It includes collecting reference data from 15 existing aircraft, estimating parameters like weight, selecting engines, designing the wing and tail, estimating lift and drag, and presenting performance characteristics. Diagrams and side views of the proposed design are also provided. The document concludes that the preliminary design addresses key considerations but that experience is important for successful aircraft design.
The document outlines the aircraft design process from initial requirements definition through detailed design, testing, and certification. It discusses establishing basic and general requirements, conducting feasibility studies, specifying detailed requirements, conceptual and preliminary design phases involving configuration selection, performance modeling, and optimization. Later phases include detailed design, ground and flight testing, and certification to clear the aircraft for intended operations. The process is iterative with frequent trade-offs and refinement of requirements and design.
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.
This document presents the final design review of an optimized sonic cruiser aircraft called the Aquila. It includes details on the aircraft layout and design, aerodynamic analysis, propulsion and performance calculations, stability and trim analysis. The aircraft is designed to carry 200 passengers with a maximum cruise speed of Mach 1 and an impressive range of over 7,600 nautical miles while cruising at altitudes above 40,000 feet. Tables and figures provide specifications, dimensions, and results of analyses on the aircraft's weight and balance, external geometry, lift and drag polars, thrust performance, static stability, and mission profiles.
1) The document outlines the iterative process of preliminary aircraft design for a military training aircraft.
2) Initial sizing used regression equations from historical data to estimate takeoff weight and wing loading.
3) Aerodynamic analysis revealed instability issues requiring design changes like increasing wing area.
4) Recalculating fuel requirements with more accuracy reduced weight and solved stability problems.
This document is a project report that analyzes and redesigns the landing gear of two light aircraft - the Piper PA28 and Grob G115. The report investigated landing gear failures using data from the Civil Aviation Authority. Finite element analysis was conducted on CAD models of the landing gears under different loading conditions. The results showed that three of the four original landing gears failed to meet safety standards. The report then redesigns the failing landing gears by changing materials and designs, and conducts new FEA to analyze if the redesigns meet standards.
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.
This document discusses subsonic flow analysis of a tailless aircraft using computational fluid dynamics (CFD). It begins with an introduction to tailless aircraft design and blended wing body (BWB) concepts. It then provides an overview of CFD, the software tools CATIA, Hypermesh, and Fluent that will be used in the analysis. The document outlines the methodology that will be followed, including designing the aircraft models in CATIA, meshing in Hypermesh, and performing CFD simulations and analysis in Fluent. It concludes that the results and discussion will provide comparisons of aerodynamic characteristics like lift, drag, pressure and velocity distributions between the tailless BWB design and a conventional aircraft design.
This document provides an overview of aircraft weight and balance processes. It defines key terms like center of gravity, moment, and maximum weights. It discusses how weight and balance must be managed on aircraft like the F-16 to ensure safety. The document demonstrates a weight and balance check on a Cessna 206 and uses iFly software to show a computational example on a Falcon 900EX. It emphasizes that operating within weight and balance limits is critical to flight safety.
To determine if a helicopter is within weight limits, a pilot must calculate the basic empty weight and consider the weight of the crew, passengers, cargo, fuel, and helicopter structure. The maximum gross weight and center of gravity range must also be checked to ensure structural integrity and safe handling. Improper loading that shifts the center of gravity outside the allowable range could cause stability and control issues. Accurate weight and balance calculations are important for safety.
This document describes the design process of a spheroid VTOL UAV. It outlines the objectives, which include designing a strong but lightweight structure within a budget of Rs 50,000. It also describes the flowchart process of designing, prototyping, testing, redesigning, manufacturing the final product, and final testing. The goals are to size the motor and propeller, integrate the flight control electronics, test and tune the flight control surfaces, and verify all objectives are met including withstanding impacts during landing.
Tutorial VSP Conference 2013, San Luis Obispo, CAHersh Amin
Vehicle Sketch Pad Structure Analysis Module (VSP SAM, http://vspsam.ae.utexas.edu/) tutorial presentation at the 2nd annual VSP (http://openvsp.org/) workshop held in San Luis Obispo, CA from Aug 7-9, 2013.
This document outlines a method for initial sizing of aircraft components. It discusses estimating the takeoff weight using statistical equations and iterating to a solution. It then describes determining the geometry of the fuselage, wing, tail surfaces, and control surfaces based on factors like the takeoff weight and engine location. Methods are provided for estimating weight fractions during different mission phases like takeoff, climb, cruise, and landing.
This document outlines the key considerations and tasks for a student design project on aircraft design. It discusses defining the problem and customers, assessing aircraft viability, understanding constraints, exploiting innovations, and organizing the design process. The document provides guidance on technical tasks like configuration selection, sizing, and drawings. It also addresses best practices for effective teamwork, such as managing meetings, assigning roles and responsibilities, and balancing individual strengths and weaknesses. The homework outlined is to summarize a textbook chapter, prepare a project plan and meeting templates, and define team member roles.
This document provides a design report for an aircraft competing in the Micro Class category of the SAE Aero Design competition. Key aspects of the design include selecting lightweight materials like balsa wood and carbon fiber to achieve a high payload fraction of around 90%. Analytical tools like Creo and Excel were used to simulate and optimize the design. A straight high wing configuration with a NACA S1223 airfoil was chosen. Performance analysis determined the aircraft needs a launch speed of around 35 mph and can fly between 40-55 mph powered by an 11" diameter propeller. The design was optimized to meet competition requirements while achieving the team's goals.
The document outlines the plans for the SAE Aero design team from Kjsce that will be competing in an annual international aerospace design competition held in Forth Worth, Texas each March. The team consists of subgroups focused on structural design, aerodynamics, materials management, and marketing/publicity. The team needs a workshop space of at least 200 square feet with a computer, various tools for one-time investment, and recurring expenses including an engine, balsa wood, transmitter radio, and batteries that total around Rs. 51,000.
The document provides an overview of the basic components and structures of aircraft, including the fuselage, wings, empennage, power plant, and landing gear. It describes the typical materials used in aircraft construction and gives examples of different structural designs for the fuselage, wings, empennage, and landing gear. Key terms related to aircraft components and structures are also defined.
This document outlines the preliminary aircraft design process, which includes selecting an aircraft category, collecting existing competition data, defining requirements and constraints, initial sizing and weight estimation, performance evaluation, initial drawings, performance analysis, cost estimation, sensitivity analysis and optimization, and proposed design homework. The process involves gathering information, establishing baseline specifications, evaluating performance against goals, analyzing tradeoffs, and proposing potential design concepts.
This document presents the design of a conceptual dual-role aircraft capable of short-haul and long-haul missions. It describes the initial weight estimation, aerodynamic analysis, performance modeling, geometry design, stability and control assessment, and conclusion that the aircraft meets the mission requirements. The appendices provide details on the mission profiles, weight breakdown, aerodynamic calculations, drag polars, performance parameters, geometry dimensions, propulsion specifications, and stability analysis.
Infinity II - Preliminary Aircraft Design PresentationManu Sharma
This document provides an overview of the geometry, mission requirements, and performance of the Infinity II aircraft. Key points include:
- The aircraft will provide aerial reconnaissance over the Galapagos Islands with a 7-hour endurance at 100+ knots and 10,000 foot ceiling.
- A canard configuration was selected for its maneuverability and stability. Computational fluid dynamics analysis showed the canard provides downwash without interfering with the wing.
- Preliminary analysis found the aircraft meets all mission requirements with a maximum takeoff weight of 1320 pounds. An 8-hour endurance was calculated.
- Stability and control analysis showed the aircraft has positive stability margins in cruise and stall conditions
The Polytechnic University of Puerto Rico's SAE Aero Design team is seeking sponsorship to participate in the 2015 SAE Aero Design West competition in California. The team will design and build a remote-controlled aircraft for the micro class competition, which requires carrying the maximum payload weight with the lowest empty aircraft weight. The sponsorship package outlines different sponsorship levels and benefits, with funds going towards materials, manufacturing, registration fees, and travel costs for the 11 student team members. The team's goal is to gain hands-on engineering experience and represent their university at the national competition.
The document provides a preliminary design for a regional passenger aircraft. It discusses the main components needed for the design, including the wing, fuselage, and empennage. For the wing, 18 key parameters are identified that must be determined, such as wing area, aspect ratio, and airfoil shape. The fuselage is designed to house passengers and cargo while withstanding cabin pressure. Key empennage parameters that require determination include the horizontal and vertical tail sizes, sweeps, and chords. The document outlines the initial steps in conceptualizing and designing a new regional aircraft.
The document discusses aircraft dimensions and measurements for the Embraer 170 and 175 aircraft. It provides details on total length, height, wing span, wing and tail areas, fuselage diameter, and distances between components. Diagrams illustrate the measurements. The aircraft use a coordinate system to define stations along the longitudinal, lateral, and vertical axes from a point of origin at the front of the aircraft.
Passenger Transport Aircraft Concept Design-FinalAlex Esche
The document describes the iterative design process for a new long-range aircraft. Over multiple tests, parameters such as fuel capacity, engine type, fuselage length, and wing design were varied to improve performance. The final proposed design incorporates composite materials, advanced systems, and a biofuel blend. It is estimated to extend major maintenance intervals by 25% compared to existing aircraft.
Design and Linear Static Analysis of Transport Aircraft Vertical Tail for Dif...IJSRD
This document summarizes the design and linear static analysis of the vertical tail structure of a transport aircraft for different rudder deflection angles. The vertical tail and rudder structure was modeled in CATIA and analyzed in MSC Patran and NASTRAN. Stresses were calculated for rudder deflections of 10, 20, and 30 degrees. The maximum principal stress was found to be well below the yield strength of the 7075-T6 aluminum alloy used, indicating the design is safe. Validation using a reserve factor approach also confirmed stresses are within acceptable limits for the expected loads on the vertical tail.
JOHNSON_BENJAMIN_11379847_Appendix CollectionBen Johnson
This document provides an appendix to a project report for the conceptual design of a two-seater electrically powered training aircraft. It includes market research on electric aircraft and training aircraft, data sheets on 29 other aircraft analyzed to help specify requirements, and details on the Cessna 152 which was used for further requirement development. The abstract indicates the data sheets contain specifications for other aircraft used to define the initial concept aircraft design.
This thesis analyzes the aerodynamic performance of a canard-configured forward swept wing aircraft design. Canards are small wings mounted in front of the main wing that act as horizontal stabilizers to control pitch. A forward swept wing directs airflow inward from the wingtips toward the root. The study selects airfoils for the canards, wing root, and wing tip based on criteria to induce earlier stalling at the root than the tips. Graphs of lift, drag, and moment coefficients versus angle of attack are presented for the reference design and two experimental airfoil sets. The second set is chosen for its larger gaps in stalling angles and higher maneuverability potential. In conclusion, a canard-configured forward
This document summarizes the design calculations for key components of a ship's rudder based on classification society rules and reference books. It provides dimensions for the rudder area, rudder force and torque, rudder stock, couplings, frames, plates, webs, pintle, bearings, and steering arrangement based on ship particulars including length, breadth, draft and speed. Calculations are shown for rudder area, force, torque and structural component sizing based on formulas from classification rules.
This document outlines the preliminary design of a light sport aircraft (LSA). Key aspects of the design include a low wing configuration with a NACA 8-H-12 airfoil, a Rotax 503 engine producing 50 hp, and a maximum takeoff weight of 1215 lbs. Performance calculations estimate a stall speed of 39 mph, maximum speed of 300 mph, and rate of climb of 13.7 ft/s. However, some parameters like service ceiling are too high due to assumptions made. Overall, with refinement to parameters like drag, the design shows promise in meeting LSA specifications.
Developing a Programme for Engine Design Calculations of a Commercial AirlinerIJMER
This project leads to a path of understanding the necessary fundamental calculations that
need to be done during an engine design of a commercial airliner. These calculations are hand based
calculations that are done based on the parameters of the airframe data provided by the airline
manufacturers. These calculations are a little tedious and require a paper and a pen to carry out the
procedures. This project will enable the following outcomes for the students: providing a fundamental
understanding of the aircraft engine design, more from the grounds up approach and an automated way
(program) of doing the above, enabling faster iterations and making it easy to achieve the required
parameters for designing an engine
This document provides a conceptual design for a hybrid aircraft called "GreyWhale" that uses wing-in-ground-effect (WIG) technology. The design aims to carry large payloads like a ship at high speeds like an aircraft. Key aspects of the conceptual design include using a blended wing body and lifting canard configuration, sizing the aircraft for a 6000-mile range while carrying a 1-million pound payload, and performing cost analysis estimating the design and production costs to be $1.161 billion. Solidworks modeling and flight performance simulations were also conducted to validate the conceptual design.
This document discusses the anatomy and performance of aircraft wings. It begins with reminders on notation used for computing aerodynamic forces on airfoils and wings. It then discusses the geometry of wings, defining terms like aspect ratio, taper ratio, sweep angle, chord, and planform area. Diagrams show how these parameters are measured on sample wing planforms. Effects of geometry on wing performance are examined, such as how aspect ratio, twist, and sweep angle influence drag and lift. Tables provide geometry parameters for real-world aircraft wings. The document emphasizes how three-dimensional wing performance differs from two-dimensional airfoil performance.
RC Plane and Aerofoil Design bst - CACULATIONS 2-1-1 (1).pdfPriyanshuYadav501002
The document provides information about a workshop on coroplast RC plane design being held by the Aero Modelling Club of NIT Kurukshetra. It includes specifications for acceptable RC plane models, such as a thrust-to-weight ratio below 0.75 and a maximum wingspan of 1.2 meters. Formulas are provided for calculating thrust, weight limits, and wing area based on the type of motor and propellers used. The document also covers topics to be discussed at the workshop, including wing design, aerofoil selection and nomenclature, tail design, relevant electronic components, and a sample circuit diagram.
The Flyin' Lion is an electric light sport aircraft designed by a team of aerospace engineering students. It has a maximum takeoff weight of 1,300 lbs, a 46 ft wingspan, and is powered by an 80 hp electric motor. Flight endurance is estimated at 2.5 hours with a range of 220 miles at sea level cruise speed. The aircraft is designed to be environmentally friendly, cost effective to operate, and suitable as a trainer aircraft.
This document summarizes the thesis submitted by Oleksandr Panasenko for a Master's degree on the design concept of a folding wingtip mechanism for civil aircraft. The thesis investigated folding wingtip designs to allow for larger wingspans while meeting airport space restrictions on the ground. Computational fluid dynamics, structural mechanics, and kinematic analyses were conducted using CAD and CAE tools to develop and test a folding wingtip design concept for a large passenger airliner with a 71.1 meter wingspan. The analyses showed the design concept was structurally sound and able to fold the wingtips to reduce the wingspan to 64.8 meters for ground operations while maintaining adequate aerodynamic and structural performance for flight.
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 describes a student project to optimize the design of a drone propeller through simulation and testing. It includes chapters on propeller aerodynamics, design considerations, CAD modeling of different propeller designs, meshing and simulation setup in Simscale, simulation results showing increased lift from designs with higher angle of attack and more blades, a test plan to evaluate resonance, and conclusions from prototype fabrication and testing.
The document analyzes the performance of an aircraft design called Azure. It assessed take-off, climb, cruise, descent and landing performance to ensure it met Airbus requirements. Key findings include:
- Climb performance of 22.7 minutes, 150nm and 2.72 tons of fuel to reach initial cruise altitude of 35,000ft.
- Cruise performance of 10.7 hours, 5215nm and 44.4 tons of fuel at a cruise climb mode.
- Descent fuel of 112kg over 135nm in 23 minutes.
- Take-off field length of 2550m at MTOW, meeting Airbus requirements.
- Landing field length of 1830m at MLW.
Optimisation of the design of uav wing j.alexander, Prakash, BSM Augustinesathyabama
The document discusses the optimization of the design of UAV wings. It analyzes two types of rectangular wings using aerodynamic and structural design methods. Aerodynamic analysis using vortex lattice modeling found lift coefficients for the wings. Structural analysis using CATIA found that using composite materials instead of isotropic materials reduced mass by 34%. The optimum design of each wing maximized strength while minimizing mass and displacement.
This document summarizes the design of an aircraft called Team Stratos Micro by a college engineering team for an aeronautics competition. The team aimed to design an aircraft weighing less than 900g that could fit in a box of specific dimensions and be powered by an electric motor. The initial design concept was for a delta wing aircraft with canards for stability. Parametric and fluid simulations as well as structural analysis were conducted to analyze the design. The first flight crashed due to longitudinal stability issues. The design was then reworked with design changes like adding flaps and rudders, and adjusting the center of gravity and canard design based on reanalyzed stability requirements.
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 document proposes a new long range supersonic bomber called the B-3 "Wraith". Key aspects of the proposed bomber include:
- Increasing maximum takeoff weight by 36% to 650,000 lbs to carry a larger payload while cruising at low supersonic speeds around Mach 1.2 at 50,000 feet with an effective mission radius of at least 3,000 miles.
- Using four upgraded GE F101 engines that together produce over 322,000 lbs of thrust, increasing thrust by over 50% compared to original engines, allowing the increased takeoff weight.
- A blended wing body design with a 1013 square meter wing employing active lift devices like flaps and a super
IRJET- Experimental and Numerical Analysis of Rectangular, Tapered and Tapere...IRJET Journal
The document presents a numerical and experimental analysis of the aerodynamic parameters like lift and drag for three wing configurations: rectangular, tapered, and tapered swept back wings. Computational fluid dynamics (CFD) was used to simulate the flow and calculate lift and drag values, which were then validated with experimental wind tunnel testing. The numerical results showed good agreement with experimental values for the rectangular and tapered wings but around a 22% error for the tapered swept wing. Overall, the rectangular wing was found to have the highest lift performance and lowest drag of the three configurations in subsonic flow.
CFD-based numerical analysis of the aerodynamic effects of a Taper wing at di...IRJET Journal
This document discusses a numerical analysis of the aerodynamic effects of wings with different taper ratios using computational fluid dynamics (CFD). The study models wings with taper ratios ranging from 0.4 to 0.8 in increments of 0.2. The CFD simulations analyze how changes in taper ratio impact lift, drag, and lift to drag ratio of the wings. Mesh independence tests are conducted to determine the appropriate mesh density for accurate results. The simulations are run at a freestream velocity of 40 m/s, yielding a Reynolds number of approximately 327931. Key findings from changing the taper ratio are discussed and comparisons are made between the aerodynamic characteristics and lift distributions of the different wing configurations.
This document summarizes an aerodynamics preliminary design review. It presents the selected airfoil, geometry, and layout for a tandem wing aircraft design. The Selig S1210 airfoil was chosen based on its high maximum lift coefficient and lift-to-drag ratio. A tandem wing configuration with an aspect ratio of 8 for the front wing and 7 for the rear wing was selected. Preliminary aerodynamic analyses of lift and drag were performed using equations from Raymer and Brandt.
This document presents the design project of a 150-seater passenger aircraft. Specifications of existing aircrafts are analyzed to determine optimum values for the design. Weight estimation is performed to calculate the take-off gross weight. The CFM56-5A1 engine is selected as the powerplant. Aerodynamic analyses include lift and drag estimation using equations. The NACA 664-221 airfoil is chosen. A narrow body fuselage and tricycle landing gear are selected. Dimensional drawings and performance parameters are provided. The project demonstrates applying aeronautical engineering principles to conceptualize an aircraft design.
This document presents the design project of a 150-seater passenger aircraft. Specifications of existing aircrafts are analyzed to determine optimum values for the design. Weight estimation is performed to calculate the take-off gross weight. The CFM56-5A1 engine is selected as the powerplant. Aerodynamic analyses include lift and drag estimation using equations. The NACA 664-221 airfoil is chosen. A narrow body fuselage and tricycle landing gear are selected. Dimensional drawings and performance parameters are provided. The project demonstrates applying aeronautical engineering principles to conceptualize an aircraft design.
Supply Chain Management for Engineers - INDE073Mohammad Tawfik
Zeco Cafe has a simple supply chain where it buys components from suppliers, mixes and serves drinks, collects money and complaints, pays suppliers for more supplies, and informs suppliers about complaints. The document discusses Zeco's supply chain risks and how it transfers risks to customers and suppliers. It also explains how Zeco adds value through food and entertainment services. Key aspects of supply chain management discussed include inventory management, forecasting, and strategies to improve distribution networks and establish information channels.
The document discusses Mohammad Tawfik's supply chain management course. It introduces Tawfik and his qualifications, then outlines the course topics, requisites, and story approach using the example of Zeco Cafe. The course will use Zeco's business problems to teach supply chain and logistics concepts. It will cover topics like logistics, transportation, warehousing and inventory management.
This document discusses concepts in supply chain management. It begins with an introduction to logistics and transportation, including different modes of transportation like ground, air, and sea. It then covers topics like warehousing, intermodal transportation, and strategies for improving supply chain performance. Throughout, different contributors provide comments and suggestions. The document also includes an assignment on designing a logistics network for a cafe business and references various sources for further information.
The document discusses inventory management and supply chain management concepts. It defines inventories as goods or materials held for future sale. It describes different types of inventories like raw materials, work-in-process, and finished goods. It also discusses inventory related to reasons like transactional efficiency, speculation, and hedging. The document also covers inventory management objectives, metrics, costs, and the economic order quantity formula.
This document outlines a course on creative problem solving and decision making. The course objectives are to identify challenges facing decision makers, recognize fundamentals of creativity skills, and apply creativity to problem solving. Topics covered include problem identification and causation, creativity and problem solving, and decision making. The document provides definitions of problems and the general problem solving framework. It also discusses techniques for problem identification like polling employees, and techniques for cause identification like five whys and fishbone diagrams. Finally, it covers creativity and innovation for problem solving, defining creativity, discussing creative people and using creativity as a business tool.
This document outlines a course for teachers on using digital content and online tools for lesson planning. It discusses identifying different resources for finding content, creating original content, and curating content from various sources while adhering to copyright restrictions. Teachers will learn how to utilize content available under creative commons licenses and incorporate curated material into their lessons.
This document outlines the content of a training of trainers course. The course aims to teach participants how to prepare training lessons, deliver training sessions, use training resources, and manage training sessions. It covers topics like learning principles, the ADDIE model of instructional design, lesson planning, preparing content, and using teaching resources. Participants will complete activities, group work and assessments including peer evaluations. The document provides learning objectives, topics, activities and instructions for various parts of the course.
The document discusses effective delegation skills. It defines delegation as assigning responsibility or authority to another person to carry out specific activities. Delegation helps develop people, allows managers to get more done, and reduces work stress. However, tasks involving highly confidential information or those delegated simply because they are disliked should not be delegated. Effective delegation requires understanding leadership, motivation, and applying the right degree of delegation based on the subordinate's skills and the task.
Why would a company hire a trainer? To produce a change. The trainer by default is
an agent for change. Regardless of any results a trainer may accomplish, the bottom line is a
measurable change in employees’ performance.
What is marketing?
How to find out about customers?
How to reach them?
How to get them to know about you?
What is a product life cycle?
How about Marketing strategies?
Learn more ...
http://AcademyOfKnowledge.org
The document discusses the process of project integration management in project management. It describes the seven major processes involved in project integration management: (1) developing the project charter, (2) obtaining project charter approval, (3) developing the project management plan, (4) directing and managing project execution, (5) monitoring and controlling project work, (6) performing integrated change control, and (7) performing project closure. It provides an overview of the inputs, tools and techniques, and outputs for each major process.
This document provides an introduction to project management. It defines a project as a temporary endeavor with a defined beginning and end, undertaken to create a unique product or service. A project manager is responsible for achieving the project's objectives and requires technical, project management, and leadership skills. Project management is the application of processes like planning, scheduling, managing, coordinating, leading, communicating, and controlling project activities to meet requirements. The document outlines some key aspects of project management like procurement, risk, quality, communication, human resources, cost, time, and scope.
The document discusses creativity and innovation. It defines creativity as coming up with new, different, or unexpected ideas. It identifies some qualities of creative people as motivation, expertise, and creative thinking skills. It also discusses several theories of creativity. The document then defines innovation as new ideas that are brought to market. It outlines different types of innovation and models of innovation management. Finally, it provides references for further reading on creativity and innovation.
Brief description of current state of drones and some future challenges.
The presentation is prepared for delivery in the "Interact with Today's World" conference held in Bibliotica Alexandria 5-6 August 2016
A review of the growth of the Israel Genealogy Research Association Database Collection for the last 12 months. Our collection is now passed the 3 million mark and still growing. See which archives have contributed the most. See the different types of records we have, and which years have had records added. You can also see what we have for the future.
How to Make a Field Mandatory in Odoo 17Celine George
In Odoo, making a field required can be done through both Python code and XML views. When you set the required attribute to True in Python code, it makes the field required across all views where it's used. Conversely, when you set the required attribute in XML views, it makes the field required only in the context of that particular view.
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How to Build a Module in Odoo 17 Using the Scaffold MethodCeline George
Odoo provides an option for creating a module by using a single line command. By using this command the user can make a whole structure of a module. It is very easy for a beginner to make a module. There is no need to make each file manually. This slide will show how to create a module using the scaffold method.
it describes the bony anatomy including the femoral head , acetabulum, labrum . also discusses the capsule , ligaments . muscle that act on the hip joint and the range of motion are outlined. factors affecting hip joint stability and weight transmission through the joint are summarized.
How to Setup Warehouse & Location in Odoo 17 InventoryCeline George
In this slide, we'll explore how to set up warehouses and locations in Odoo 17 Inventory. This will help us manage our stock effectively, track inventory levels, and streamline warehouse operations.
A workshop hosted by the South African Journal of Science aimed at postgraduate students and early career researchers with little or no experience in writing and publishing journal articles.
How to Fix the Import Error in the Odoo 17Celine George
An import error occurs when a program fails to import a module or library, disrupting its execution. In languages like Python, this issue arises when the specified module cannot be found or accessed, hindering the program's functionality. Resolving import errors is crucial for maintaining smooth software operation and uninterrupted development processes.
This presentation was provided by Steph Pollock of The American Psychological Association’s Journals Program, and Damita Snow, of The American Society of Civil Engineers (ASCE), for the initial session of NISO's 2024 Training Series "DEIA in the Scholarly Landscape." Session One: 'Setting Expectations: a DEIA Primer,' was held June 6, 2024.
How to Add Chatter in the odoo 17 ERP ModuleCeline George
In Odoo, the chatter is like a chat tool that helps you work together on records. You can leave notes and track things, making it easier to talk with your team and partners. Inside chatter, all communication history, activity, and changes will be displayed.
Executive Directors Chat Leveraging AI for Diversity, Equity, and InclusionTechSoup
Let’s explore the intersection of technology and equity in the final session of our DEI series. Discover how AI tools, like ChatGPT, can be used to support and enhance your nonprofit's DEI initiatives. Participants will gain insights into practical AI applications and get tips for leveraging technology to advance their DEI goals.
How to Manage Your Lost Opportunities in Odoo 17 CRMCeline George
Odoo 17 CRM allows us to track why we lose sales opportunities with "Lost Reasons." This helps analyze our sales process and identify areas for improvement. Here's how to configure lost reasons in Odoo 17 CRM
3. Problem definition
• A military training aircraft
• Load factors +6 & -3G
• Two pilots, 105 Kg each
• Baggage 22.5 Kg
• Takeoff distance of 1500 m
• Climb to 5000 m
• Cruise 15 min at a speed of no less than 87 m/s
• Manoeuvre at 103 m/3 for 60 min
• Return to base
• Taxi and parking
Aero474
Aircraft Design
4. Data Collection
● Data of 30 different aircraft was collected
● Some relations were plotted and
regression relations were calculated
Aero474
Aircraft Design
5. Thrust History
1.2
1
0.8
T /T ma x(25.98 KN)
0.6
0.4
0.2
0
1955 1960 1965 1970 1975 1980 1985 1990 1995
Ye a r
Aero474
Aircraft Design
6. Empty to Take-off weight
0.8
0.75
0.7
0.65
W o/W e
0.6
0.55
0.5
0.45
0.4
1000 2000 3000 4000 5000 6000 7000 8000 9000
W o (Kg)
Aero474
Aircraft Design
7. Wing loading vs aspect ratio
550
500
450
400
350
L (Kg/ m^2)
300
250
200
150
100
4 4.5 5 5.5 6 6.5 7
AR
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Aircraft Design
9. Preliminary Sizing
● Using the relations obtained from the data,
equations could be obtained to fill in the
equation
● W o=W e W f W pW c
● You obtain a quadratic equation in the
take-off weight which can be solved readily
● The number was 3220 Kg
Aero474
Aircraft Design
10. Preliminary Sizing
● Similarly, the wing loading could be found
2
to be: 290 Kg/m
● From which you get the wing area to be 11
m2
● Which yields and Aspect ratio of 5 and
span of 7.5 m
Aero474
Aircraft Design
11. Geometric Considerations
● From the data collected, the taper ratio of
0.5 was used
● The distance between the tail and the is,
similarly, taken to be 3 times the mean
wing chord
● For the area of the stabilizers, the volume
ratio was the determinant as per a
reference and taken as 0.7
Aero474
Aircraft Design
17. Components Weight
● Formulae are given in different references
to estimate the weight of different
components
● What is really important is the weight
distribution
● The distribution of the masses of the
aircraft will be assumed to be regular as
per the external size
Aero474
Aircraft Design
20. Aerodynamic Performance
Estimation
● The Aerodynamic coefficients may be
evaluated using different methods
● There are simple formulae to determine
them
● You may use some Lattice methods to
estimate the coefficients
● You may solve the full Navier Stokes
equations!
Aero474
Aircraft Design
21. For the Example
● Selection of the aerofoil was NACA4212
for the wing and NACA0009 for the tail.
● Using Prandtl lifting line theory, the wing
and tail lift coefficients were calculated
● The induced drag coefficient was also
evaluated using the same theory
● Finally, the maximum lift coefficient was
calculated using emperical relations.
Aero474
Aircraft Design
22. Total Coefficients
● Finally, the total lift, drag, and moment
coefficients were calculated
● BUT … Flight stability literature indicated
that the moment and lift coefficients were
not adequate!
● First modification was to change the tail
incidence angle
Aero474
Aircraft Design
26. CRITICAL!!!
● Reviewing those results, it was found that
the lift coefficient at cruise conditions is so
much near the maximum!
● To remedy this problem, the wing loading
was reduced!
● Increasing the area of the wing, changed
EVERYTHING!!!
Aero474
Aircraft Design
28. Flight Dynamics and Stability
● Now that we have all the aerodynamic
coefficients, we may approach the problem
of dynamics of the aircraft
Aero474
Aircraft Design
29. Longitudinal Dynamics &
Stability
● The Response for an impulse elevator
input could be plotted using the Runge-
Kutta method
● The two main modes of motion of the
aircraft in longitudinal direction are:
● Phugoid
● Short period
Aero474
Aircraft Design
32. Third iteration!
● Now, the aircraft need to be modified again!
● However, before doing all that effort again, let's
examine the weight requirements of the fuel
● When recalculating the fuel requirements using
detailed relations for each step of the mission,
the weight was reduced
● That lead to the stability of the aircraft!
● Fuel weight was reduced by more than 50%!!!
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Aircraft Design
33. Aerodynamic Refinement
● A VLM code was developed for the
aerodynamic analysis of aircraft
components
● The results obtained for the combined
wing-tail problem gave better estimates for
the aerodynamic characteristics
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Aircraft Design
41. Other Parameters
● Range
● Endurance
● Flight in a horizontal circle
● Take-off runway
● Stall speed
● Time to reach 5000 m
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Aircraft Design
46. Cost Estimates
● Engineering hours
● Tooling hours
● Manufacturing hours
● Quality control hours
● Development Support
● Flight test cost
● Material cost
● Avionics
● Engine
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Aircraft Design
47. Homework #5
● Prepare a 30 minutes presentation
● Presentation includes all your work up to
this point
● History, data, project plan, etc...
● Plus preliminary weight estimations and
geometric considerations
Aero474
Aircraft Design