This document contains a report on the design, construction and flight of a paper glider as part of an integrated assignment. It describes the conceptual design of the glider, including the wing shape and dimensions. It also includes calculations of the glider's centre of gravity, lift and drag forces. Details are provided on the aerodynamic design of the wings and tail as well as the structural design and estimated weight.
Atmosphere: Properties and Standard Atmosphere | Flight Mechanics | GATE Aero...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/DqaoNt0LoIE
The topics covered in this session are, Properties of Atmosphere, International Standard Atmosphere (ISA) definition and derivation, ISA Chart. The formula for obtaining ISA Chartar completely derived from basic equations.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
This document provides a protocol for agar electrophoresis. It lists the required materials which include agar powder, TAE buffer solution, gel chamber, comb, samples, and power supply. The process involves preparing the TAE buffer, casting the agar gel, loading colored samples into the wells, running the gel at 50V for 15 minutes, and observing how far the different samples migrate through the gel. The conclusion is that electrophoresis separates samples by size and charge, with smaller, more negatively charged components migrating farther towards the positive anode. By comparing the band patterns of crime scene and suspect samples, one sample matched the crime scene.
Banditry involved private acts of delinquency, while corsairs received state support to plunder enemies. In the 16th and 17th centuries, corsairs from North Africa and the Ottoman Empire attacked Catalan villages, interrupting trade. Catalans organized their own defenses, increasing galley production. Bandits fell into categories like adventurers seeking danger, smugglers forced by necessity, and thieves targeting the rich. The bubonic plague in 1650 decreased the population and economy, leading some to turn to banditry out of poverty. On land, bandit groups posed dangers, while at sea, corsairs and pirates raided through pillaging and plundering.
Dubai is the largest city in the United Arab Emirates, located on the Persian Gulf coast. It has less than 1500 square kilometers of area and is divided into two regions by Dubai Creek. Dubai has experienced rapid economic growth since the 1960s due to oil discovery, making it now one of the most important cities in the world. It is considered one of the most modern cities globally, known for skyscrapers like the world's tallest building, Burj Khalifa. Islam plays a central role in Dubai's culture and daily life. Local cuisine includes dishes like shawarma and fala-fil accompanied by juices and desserts.
This resume is for Subhash Dheer, who has over 28 years of experience in quality assurance, quality control, site management, and construction management for civil and infrastructure projects in the Middle East, Afghanistan, and India. He is currently the QC Manager for Turner International working on an air force station project in India. Previously he has held roles as QC Manager, Project Manager, and Country Quality Control Manager for several US-based firms working on projects in Afghanistan. His experience includes establishing and managing QA/QC programs, attending project meetings, performing submittal reviews, and ensuring compliance with quality standards.
Atmosphere: Properties and Standard Atmosphere | Flight Mechanics | GATE Aero...Age of Aerospace
For Video Lecture of this presentation: https://youtu.be/DqaoNt0LoIE
The topics covered in this session are, Properties of Atmosphere, International Standard Atmosphere (ISA) definition and derivation, ISA Chart. The formula for obtaining ISA Chartar completely derived from basic equations.
Attention! "Gate Aerospace Engineering aspirants", A virtual guide for gate aerospace engineering is provided in "Age of Aerospace" blog for helping you meticulously prepare for gate examination. Respective notes of individual subjects are provided as 'Embedded Google Docs' which are frequently updated. This comprehensive guide is intended to efficiently serve as an extensive collection of online resources for "GATE Aerospace Engineering" which can be accessed free of cost. Use the following link to access the study material
https://ageofaerospace.blogspot.com/p/gate-aerospace.html
This document provides a protocol for agar electrophoresis. It lists the required materials which include agar powder, TAE buffer solution, gel chamber, comb, samples, and power supply. The process involves preparing the TAE buffer, casting the agar gel, loading colored samples into the wells, running the gel at 50V for 15 minutes, and observing how far the different samples migrate through the gel. The conclusion is that electrophoresis separates samples by size and charge, with smaller, more negatively charged components migrating farther towards the positive anode. By comparing the band patterns of crime scene and suspect samples, one sample matched the crime scene.
Banditry involved private acts of delinquency, while corsairs received state support to plunder enemies. In the 16th and 17th centuries, corsairs from North Africa and the Ottoman Empire attacked Catalan villages, interrupting trade. Catalans organized their own defenses, increasing galley production. Bandits fell into categories like adventurers seeking danger, smugglers forced by necessity, and thieves targeting the rich. The bubonic plague in 1650 decreased the population and economy, leading some to turn to banditry out of poverty. On land, bandit groups posed dangers, while at sea, corsairs and pirates raided through pillaging and plundering.
Dubai is the largest city in the United Arab Emirates, located on the Persian Gulf coast. It has less than 1500 square kilometers of area and is divided into two regions by Dubai Creek. Dubai has experienced rapid economic growth since the 1960s due to oil discovery, making it now one of the most important cities in the world. It is considered one of the most modern cities globally, known for skyscrapers like the world's tallest building, Burj Khalifa. Islam plays a central role in Dubai's culture and daily life. Local cuisine includes dishes like shawarma and fala-fil accompanied by juices and desserts.
This resume is for Subhash Dheer, who has over 28 years of experience in quality assurance, quality control, site management, and construction management for civil and infrastructure projects in the Middle East, Afghanistan, and India. He is currently the QC Manager for Turner International working on an air force station project in India. Previously he has held roles as QC Manager, Project Manager, and Country Quality Control Manager for several US-based firms working on projects in Afghanistan. His experience includes establishing and managing QA/QC programs, attending project meetings, performing submittal reviews, and ensuring compliance with quality standards.
Ulan Bator is the capital and largest city of Mongolia, with a population over 1.3 million. It is located in north central Mongolia at an elevation of 1,310 meters in a valley on the Tuul River. While houses in Ulan Bator are modern and tall, Mongolian nomads traditionally live in portable round tents called yurts. Restaurants serve Chinese and Korean foods like rice and soup, but traditional Mongolian cuisine features vegetables, dairy, and meats from camels, goats, horses, lambs, and yaks.
This resume is for Ketan Patel, who has 17 years of experience in the plastics industry working in screen printing, pad printing, and hot stamping. He currently works as a printing in-charge at Jambo Plastics in Tanzania, East Africa. Previously he worked at Clear Plastics Industries Ltd. in India. Ketan is seeking a challenging position that allows him to utilize and improve his skills. He has strong skills in printing production planning and quality control.
Strategic design of aircraft wings have evolved over time for maximum fuel efficiency. One of such ideas involves winglet which has been known
to reduce turbulence at the tip of the wings. This study intends to investigate the
differences in drag and lift forces generated at aeroplane wings with and without winglet at cruising speed using FEM. Simulations were performed in the
SST turbulence model of CFD and the results are compared to that of the experimental and theoretical models. The simulation showed that the lift increased
by 26.0% and the drag decreased by 74.6% for the winglet at cruising speed.
Development of a Integrated Air Cushioned Vehicle (Hovercraft)IJMER
1) The document describes the development of an integrated air cushion vehicle (hovercraft) prototype. It details the design of major components like the hull, skirt, air box, engine assembly, and integrated lift and thrust system using one propeller.
2) Calculations are shown for determining the required air volume, pressures, and component sizes based on the hovercraft's weight and dimensions. A suitable impeller is selected to provide the needed airflow and pressure.
3) Fabrication of the prototype from materials like plywood, polystyrene, and aluminum is described. Testing showed the hovercraft could lift and propel itself carrying 75kg at 70mm above the surface at near 20km/hr.
The document discusses an experiment to compare the turn performance of an RC airplane using ailerons versus using just the rudder. Flight tests were conducted to measure the turn rate for each case using a GPS data logger. Results showed the turn rate varied more when using ailerons but peak rates were mostly higher than when using just the rudder, indicating improved performance with the addition of ailerons. Some modifications were made to strengthen the wing and increase power to accommodate the added weight of the aileron control surfaces.
The document summarizes a computational fluid dynamics study of flow over clean and loaded wings using ANSYS Fluent. It describes simulating flow over an airfoil at angles from 0-20 degrees both with and without a missile model attached. The results show that boundary layer separation begins around 15 degrees for the clean wing and occurs at a lower angle for the loaded wing. However, issues with meshing prevented analysis of the loaded wing case. Increasing angle of attack was found to increase lift forces until stall occurred due to vortex shedding beyond 20 degrees.
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.
Optimizationof fuselage shape for better pressurization and drag reductioneSAT Journals
Abstract
The fuselage of any aircraft is essentially to accommodate the payload. It is normally not as streamlined as the wing. Cabin pressurization has been a major concern in the manufacturing of aircrafts. Generally, a cylindrical shape is preferred from a pressurization point of view as it has a higher strength and weighs less too. On the other hand, a sphere is considered as the best pressure vessel among all the shapes, but, sphere being a bluff body is not suitable for carrying payloads. On this note, a cylinder is considered to be better than a sphere to carry the payload and mainly to achieve a streamlined flow. In this paper, the shape chosen is a combination of the sphere and the cylinder to achieve optimum results for pressurization as well as a better streamlined flow. Our prime aim is to convert this bluff body into something more efficient and useful, rather than only for carrying the payload. We have focused basically on two details viz. 1) Better Pressurization and 2) to assist in minimizing the drag, thereby increasing the overall lift of the aircraft and hence increasing the fuel efficiency. The proposed fuselage structure was designed in CATIA V5 software and structural analyses were done in Auto-Desk Multi-Physics software. As a result, a better structural load capacity was found. A load of 10 N/mm2 was applied on both the bodies under consideration (cylinder and ellipse) having the same material, surface area, volume and weight. For the proposed elliptical design, 78% reduction in the minimum stress value and 10% reduction in the maximum stress value were noticed.
Keywords: Fuselage, Lifting Fuselage, Drag Reduction, Pressurization, Hoop Stress, Multi body design, Toroidal Shells, Multi-cylinder, Channel Propeller Configuration, Carbon Fiber, Graphite Fiber, Stabilization and Carbonization.
International Journal of Computational Engineering Research(IJCER)ijceronline
International Journal of Computational Engineering Research(IJCER) is an intentional online Journal in English monthly publishing journal. This Journal publish original research work that contributes significantly to further the scientific knowledge in engineering and Technology.
This was my final year project thesis, based on the results from NASA Langley Research Centre’s work on the PRANDTL-D project which was into minimizing the induced drag of a wing body along with elimination of adverse yaw.
A Good Effect of Airfoil Design While Keeping Angle of Attack by 6 Degreepaperpublications3
Abstract: Airfoil is a shape of wing or blade of (a propeller, rotor or turbine) by which a fluid generates an aerodynamic force. The component of this force perpendicular to the direction of its speed is called lift force and the component parallel to its speed is called drag forces. Here we see that if we set the angle of attack by 6 degree in fluid NACA0012 we found the aerodynamic forces with suitable positive result our research is totally based on iterations method and based on the help of cfd software.
Ulan Bator is the capital and largest city of Mongolia, with a population over 1.3 million. It is located in north central Mongolia at an elevation of 1,310 meters in a valley on the Tuul River. While houses in Ulan Bator are modern and tall, Mongolian nomads traditionally live in portable round tents called yurts. Restaurants serve Chinese and Korean foods like rice and soup, but traditional Mongolian cuisine features vegetables, dairy, and meats from camels, goats, horses, lambs, and yaks.
This resume is for Ketan Patel, who has 17 years of experience in the plastics industry working in screen printing, pad printing, and hot stamping. He currently works as a printing in-charge at Jambo Plastics in Tanzania, East Africa. Previously he worked at Clear Plastics Industries Ltd. in India. Ketan is seeking a challenging position that allows him to utilize and improve his skills. He has strong skills in printing production planning and quality control.
Strategic design of aircraft wings have evolved over time for maximum fuel efficiency. One of such ideas involves winglet which has been known
to reduce turbulence at the tip of the wings. This study intends to investigate the
differences in drag and lift forces generated at aeroplane wings with and without winglet at cruising speed using FEM. Simulations were performed in the
SST turbulence model of CFD and the results are compared to that of the experimental and theoretical models. The simulation showed that the lift increased
by 26.0% and the drag decreased by 74.6% for the winglet at cruising speed.
Development of a Integrated Air Cushioned Vehicle (Hovercraft)IJMER
1) The document describes the development of an integrated air cushion vehicle (hovercraft) prototype. It details the design of major components like the hull, skirt, air box, engine assembly, and integrated lift and thrust system using one propeller.
2) Calculations are shown for determining the required air volume, pressures, and component sizes based on the hovercraft's weight and dimensions. A suitable impeller is selected to provide the needed airflow and pressure.
3) Fabrication of the prototype from materials like plywood, polystyrene, and aluminum is described. Testing showed the hovercraft could lift and propel itself carrying 75kg at 70mm above the surface at near 20km/hr.
The document discusses an experiment to compare the turn performance of an RC airplane using ailerons versus using just the rudder. Flight tests were conducted to measure the turn rate for each case using a GPS data logger. Results showed the turn rate varied more when using ailerons but peak rates were mostly higher than when using just the rudder, indicating improved performance with the addition of ailerons. Some modifications were made to strengthen the wing and increase power to accommodate the added weight of the aileron control surfaces.
The document summarizes a computational fluid dynamics study of flow over clean and loaded wings using ANSYS Fluent. It describes simulating flow over an airfoil at angles from 0-20 degrees both with and without a missile model attached. The results show that boundary layer separation begins around 15 degrees for the clean wing and occurs at a lower angle for the loaded wing. However, issues with meshing prevented analysis of the loaded wing case. Increasing angle of attack was found to increase lift forces until stall occurred due to vortex shedding beyond 20 degrees.
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.
Optimizationof fuselage shape for better pressurization and drag reductioneSAT Journals
Abstract
The fuselage of any aircraft is essentially to accommodate the payload. It is normally not as streamlined as the wing. Cabin pressurization has been a major concern in the manufacturing of aircrafts. Generally, a cylindrical shape is preferred from a pressurization point of view as it has a higher strength and weighs less too. On the other hand, a sphere is considered as the best pressure vessel among all the shapes, but, sphere being a bluff body is not suitable for carrying payloads. On this note, a cylinder is considered to be better than a sphere to carry the payload and mainly to achieve a streamlined flow. In this paper, the shape chosen is a combination of the sphere and the cylinder to achieve optimum results for pressurization as well as a better streamlined flow. Our prime aim is to convert this bluff body into something more efficient and useful, rather than only for carrying the payload. We have focused basically on two details viz. 1) Better Pressurization and 2) to assist in minimizing the drag, thereby increasing the overall lift of the aircraft and hence increasing the fuel efficiency. The proposed fuselage structure was designed in CATIA V5 software and structural analyses were done in Auto-Desk Multi-Physics software. As a result, a better structural load capacity was found. A load of 10 N/mm2 was applied on both the bodies under consideration (cylinder and ellipse) having the same material, surface area, volume and weight. For the proposed elliptical design, 78% reduction in the minimum stress value and 10% reduction in the maximum stress value were noticed.
Keywords: Fuselage, Lifting Fuselage, Drag Reduction, Pressurization, Hoop Stress, Multi body design, Toroidal Shells, Multi-cylinder, Channel Propeller Configuration, Carbon Fiber, Graphite Fiber, Stabilization and Carbonization.
International Journal of Computational Engineering Research(IJCER)ijceronline
International Journal of Computational Engineering Research(IJCER) is an intentional online Journal in English monthly publishing journal. This Journal publish original research work that contributes significantly to further the scientific knowledge in engineering and Technology.
This was my final year project thesis, based on the results from NASA Langley Research Centre’s work on the PRANDTL-D project which was into minimizing the induced drag of a wing body along with elimination of adverse yaw.
A Good Effect of Airfoil Design While Keeping Angle of Attack by 6 Degreepaperpublications3
Abstract: Airfoil is a shape of wing or blade of (a propeller, rotor or turbine) by which a fluid generates an aerodynamic force. The component of this force perpendicular to the direction of its speed is called lift force and the component parallel to its speed is called drag forces. Here we see that if we set the angle of attack by 6 degree in fluid NACA0012 we found the aerodynamic forces with suitable positive result our research is totally based on iterations method and based on the help of cfd software.
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
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
This document analyzes the aerodynamic performance of blended winglets on aircraft wings through computational fluid dynamics modeling. It finds that winglets can increase the lift to drag ratio of wings by 6-15% compared to wings without winglets. The maximum efficiency occurs at a winglet cant angle of 45 degrees and an angle of attack of 4 degrees. CFD simulations are validated against experimental data and show good agreement on lift coefficient values. Winglets improve efficiency by reducing wingtip vortices and increasing effective aspect ratio without adding structural weight.
It is a major project report on DIFFERENT TYPES OF WINGLETS AND THEIR CORRESPONDING VORTICES, and it can be helpful for a person looking for specifically about winglet and vortex formation and relation among them. It is a very good source for aerospace engineering student as well coz they will get to knew about vortex and winglet.
1) The document is a project report submitted by Imtisal Ahmad to Engr. Abdul Haadi on a parachute project. It includes an introduction, research conducted, design details, technical aspects of parachute equations, and layout considerations.
2) The report explains the basic physics of parachutes and how to calculate the necessary parachute diameter and descent velocity based on parameters like mass, air density, and desired impact speed.
3) Details are provided on designing and constructing different types of parachutes, including hemispherical and elliptical designs. Equations are presented to calculate parachute performance at different altitudes.
This document provides details on the design of a 1-seater military aircraft. It discusses the aircraft's specifications including its weight, performance characteristics, and dimensions of the wing. It also summarizes the structural analysis and material selection for the fuselage and wings. Several chapters describe the preliminary and detailed design of the aircraft's wing, fuselage, and tail section. Load distributions and structural components of each section are analyzed.
Aerodynamic Performance Analysis of a Co-Flow Jet Aerofoil using CFDIRJET Journal
This document discusses a computational fluid dynamics (CFD) analysis of a co-flow jet aerofoil design intended to enhance aerodynamic performance. The analysis compares the lift, drag, and stall characteristics of a baseline aerofoil to a modified co-flow jet aerofoil design. The co-flow jet aerofoil incorporates jets of high-pressure air injected towards the leading edge and sucked from the trailing edge, maintaining zero net mass flux across the aerofoil. This is intended to increase circulation and lift while decreasing drag. The CFD analysis is conducted using Reynolds-averaged Navier-Stokes equations to simulate performance at various angles of attack. Preliminary results suggest the co-flow jet design achieves
International Journal of Engineering Research and DevelopmentIJERD 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.
This document discusses determining the aerodynamic characteristics of the FX63-137 airfoil experimentally and through computer simulation. The airfoil was manufactured using a CNC machine and tested in a subsonic wind tunnel at speeds of 20m/s and 30m/s. The results were compared to simulations run using the XFOIL program. The analyses found that the best lift coefficients were 1.677586 at 12 degrees angle of attack for 20m/s wind speed and 1.681103 at 12 degrees for 30m/s, indicating maximum lift for the airfoil is achieved at those conditions.
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.
Similar to KT1A-IO3-Beentjes-Berends-DeDecker-VanderGalien-Savenije (20)
2. Verslag
bij de integrerende opdracht
ontwerp, bouw en vlieg een papieren modelzweefvliegtuig
Naam Nick Beentjes Studentnr. 500715585
Naam Jeroen Berends Studentnr. 500703406
Naam Glenn De Decker Studentnr. 500705423
Naam Marnix van der Galien Studentnr. 700502957
Naam Bart Savenije Studentnr. 500704428
1. Geef een beschrijving van jullie conceptuele ontwerp, inclusief een beschouwing
over de functie en de vorm van jullie vliegtuigje. Leg een verband tussen de
ontwerpeis voor een zo lang mogelijke vliegtijd en de ontwerpparameters.
The main objective of the assignment is to design and build a glider which can use the potential
energy as efficient as possible and convert said force to kinetic energy to conserve height,
staying aloft as long as possible. The Kinetic or speed energy is converted into lift by the airfoil,
consequently reducing the rate of which height is lost. The actors considered to contribute to the
maximization of the distance traveled are:
• the shape of the wing
• the aspect ratio
• the aircraft weight
• the aircraft shape
Considering these factors, low weight, a sleek aircraft body and using a thin wing profile with a
high aspect ratio will maximize the gliding distance. Designing our sail plane we opted for a wing
root structure at the center of the body. The wings are connected through a wing truss (figure 1)
and the empennage is connected by a single beam (figure 2), enforced by the aircraft
monocoque structure ensuring structural integrity. The long wings are high in aspect ratio and
are mounted in dihedral to facilitate positive stability. The rudder and elevator are attached to the
skeleton through two incisions to insure sound attachment to the structure. (figure 3)
Figure 1: Wing root structure Figure 2: Beam structure Figure 3: Empennage
3. Using the straws to build beams for the wing, we opted to cut the straws in half to save weight,
which ultimately reduces the amount of lift needed and the induced drag that is created. This will
increase the strength of the structure and increase the gliding distance of the sail plane.
The monocoque structure is also designed to use the least amount of paper as possible and
using a sharp nose cone, we are able to reduce the form drag in the front of the aircraft.
2. Geef een overzicht van jullie fysische berekeningen, te beginnen met een VLS van
jullie vliegtuig tijdens de vlucht. Laat zien hoe jullie het vliegtuigje in evenwicht
houden.
Before we can make balance calculations, the centre of gravity of the aircraft has to be
assessed. For stable flight it is important that the centre of gravity lies in front of the wing. When
a stall occurs the aircraft’s nose decreases in angle of attack providing an increase in speed and
will recover from the stall. For the substantiation of the calculation of the centre of gravity,
please refer to the annex. According to the calculations shown in the annex, that the centre of
gravity lies at 0.00307 meters referenced from the middle of the aircraft in front of the wing.
In order to maintain a balanced flight, lift should equal weight. Furthermore the moment of the lift
of the wing should equal the moment of the downforce of the stabilizer to prevent undesirable
rotations around the lateral axis.
One can see that this is indeed the case with our aircraft in the free body diagram shown in the
annex. The wings of the aircraft are designed so that lift equals weight (further information
regarding wing design can be found in ‘opdracht 3.3’.) To prevent the aircraft from rotating, the
following equation should be applied :
Ideally this equation equals zero, however if this equation cannot equal zero for practical
reasons, it is desirable that the result of this equation is a little below zero. This means that the
moment of the down force is slightly greater than the moment of the lift, which results in a
clockwise rotation around the centre of gravity. Thus, a slight upward pitch. A counter clockwise
rotation is less desirable, as our wing Is angled at zero degrees geometrical angle of attack.
Thus if a downward pitch is used it would position the wing at or below the point of zero effective
angle of attack.
Filling our design parameters into the equation,
yields:
4. Note that the result of the equation is below zero but negligible.
5. 3. Geef een toelichting op het aerodynamische ontwerp, inclusief berekeningen van de
benodigde afmetingen van vleugel en staartvlakken.
For our aerodynamic design we have chosen for an angle of incidence of zero degrees. This
angle of attack give a CL-value of 0,4375, according to the wind tunnel lab with a Clarck Y-14
profile (shown in the CL graph). Shown in the CL/CD graph, an angle of incidence of zero
degrees gives the lowest value. The lift force is calculated by approximating the mass the aircraft
in order to maximize the flight distance.
With the CL value the wing area can be calculated:
T = 20 degrees = 293 degrees Kelvin ; Standard temperature of 287 in degrees Kelvin
Atmospheric pressure = 99.600 Pascal ; Air density; Rho: 99600 / (287*293) = 1,18443115
kg/m3
Lift = total weight = 0,365057 N ; Speed = 5,5 m/s ; CL = 0,4375
S (Wing area needed): S = 0,365057 / (0,5*1,18443115*5,5^2*0,4375) =0,04657763 m2.
Ultimately we opted for wings that are 40 cm long and 6 cm wide on both sides. This leads to a
total wing area of 0,048 square meters. Using this configuration the aircraft has more wing area
than that is needed, resulting in a smaller loss of altitude as speed decreases. The wings are
square shaped, with high aspect ratio, ensuring the least amount of resistance. The tail section is
8 by 3 cm giving a total area of 0,0024 m2. This generates a negative lift of:
L = 0,024 * 0,5*1,18443115*5,5^2*0,4375 = 0,018810247 N
The nose of the glider is shaped in such a manner that the aircraft is as sleek as possible
decreasing the parasitic drag.
6. 4. Geef een toelichting op het constructief ontwerp, inclusief bouwschetsen.
The paper aircraft is based on modern gliders. When looking at the aircraft design from above, a
slight water drop shape is apparent. The building materials used are: 80 g/m2 paper, plastic
straws and glue. The sailplane was designed with a wing root structure at the center of the
aircraft with as a backbone, a single straw that runs from the wing root to the empennage.
Ensuring a strong wing, a vertical straw is placed every 29mm glued perpendicular to the
horizontal straw that runs from the wing root to the wing tip as shown in the schematic. To save
weight the wing spars are ¼ diameter of a straw. The stabilizer is constructed in a similar way;
however the spars are placed 14mm apart and mounted to a separate wing root structure similar
to the main wing root.
5. Wat is het geschatte gewicht van jullie ontwerp? Beschrijf hoe jullie dit hebben
vastgesteld.
We approximated the weight of the glider, by calculating the weight of the paper that will be used
to construct the airfoil and fuselage. The straws where bundled and weighed to calculate the
weight of a single straw. Using this data we calculated the amount of material needed and
entered these values into excel to find the total weight of the aircraft. Taking the glue into
consideration, which accounts of 45% of the total weight, we estimated the total weight of the
aircraft to be 0,3650 Newton. The weight of the wing is calculated per 10 cm. To approximate the
total weight of the wing this must be multiplied by the total wing length. These calculations can
be found in the appendix.