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.
NASA and its industry partners are investigating a blended wing aircraft concept for potential use as a future air transport for both civilian and military applications. https://www.nasa.gov/centers/langley/news/factsheets/FS-2003-11-81-LaRC.html
CFD Studies of Blended Wing Body Configuration for High Angles of Attack -- Z...Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
Blended Wing Body (BWB) configurations offer a unique advantage of generating lift from the fuselage. The research paper aims to study several configurations aerodynamically for the viability of use in actual flight. The code is validated using the configuration from UiTM Malaysia. Simulations are performed at high angles of attack ranging from 20 deg to 40 deg. Good agreement is seen in RANS CFD and low speed wind tunnel data. The comparison gives confidence that BWB can be simulated at high angles of attack. Authors - Irshad Khan and Deepak Patil (Zeus Numerix), DN Santhosh (SDM CoE)
NASA and its industry partners are investigating a blended wing aircraft concept for potential use as a future air transport for both civilian and military applications. https://www.nasa.gov/centers/langley/news/factsheets/FS-2003-11-81-LaRC.html
CFD Studies of Blended Wing Body Configuration for High Angles of Attack -- Z...Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
Blended Wing Body (BWB) configurations offer a unique advantage of generating lift from the fuselage. The research paper aims to study several configurations aerodynamically for the viability of use in actual flight. The code is validated using the configuration from UiTM Malaysia. Simulations are performed at high angles of attack ranging from 20 deg to 40 deg. Good agreement is seen in RANS CFD and low speed wind tunnel data. The comparison gives confidence that BWB can be simulated at high angles of attack. Authors - Irshad Khan and Deepak Patil (Zeus Numerix), DN Santhosh (SDM CoE)
A Blended Wing Body (BWB) aircraft is a configuration where the wing and fuselage are integrated which essentially results in a large flying wing. BWB aircraft were previously called ‘tailless airplanes’ and ‘Flying-Wing aircraft’. The BWB configuration has shown promise in terms of aerodynamic efficiency, in particular for very large transport aircraft, because the configuration has a single lifting surface that means an aerodynamically clean configuration.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
In recent years, air transportation has increased between major cities. Conventional aircraft's lack fuel efficiency, high Lift to Drag (L/D) ratio, high payload carrying capacity since there has not been a major technological breakthrough in aerodynamic geometry. Hence, there has been a need to develop a new composite structure to push the boundaries of current technologies and to breathe new life into civil transportation. Blended Wing Body (BWB) bridges the gap between future requirements. The BWB configuration is a new concept in aircraft design which provides greater internal volume, aerodynamics and structural efficiency, noise reduction, and most importantly significant improvement on cost-per-seat-mile. The design approach of BWB is to maximize overall efficiency by integrating the propulsion systems, wings, and the body into a single lifting surface. BWB is a unique tailless single entity where the fuselage is merged with wing and tail. Blended wing body has flattened and airfoil surface which contributes higher lift than conventional ones. The objective of this paper is to study aerodynamic study of blended wing body layout.
The presentation was prepared for an Technical Paper Presentation competition. It contains basic conceptual explanations pertaining to the BWB concept.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
Free eBook - Websites For B2 B Technogy CompaniesKim Walowsky
A complete and cost-effective web design, build and maintenance service designed to meet the specific needs of high-tech companies operating in B2B markets
A Blended Wing Body (BWB) aircraft is a configuration where the wing and fuselage are integrated which essentially results in a large flying wing. BWB aircraft were previously called ‘tailless airplanes’ and ‘Flying-Wing aircraft’. The BWB configuration has shown promise in terms of aerodynamic efficiency, in particular for very large transport aircraft, because the configuration has a single lifting surface that means an aerodynamically clean configuration.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
In recent years, air transportation has increased between major cities. Conventional aircraft's lack fuel efficiency, high Lift to Drag (L/D) ratio, high payload carrying capacity since there has not been a major technological breakthrough in aerodynamic geometry. Hence, there has been a need to develop a new composite structure to push the boundaries of current technologies and to breathe new life into civil transportation. Blended Wing Body (BWB) bridges the gap between future requirements. The BWB configuration is a new concept in aircraft design which provides greater internal volume, aerodynamics and structural efficiency, noise reduction, and most importantly significant improvement on cost-per-seat-mile. The design approach of BWB is to maximize overall efficiency by integrating the propulsion systems, wings, and the body into a single lifting surface. BWB is a unique tailless single entity where the fuselage is merged with wing and tail. Blended wing body has flattened and airfoil surface which contributes higher lift than conventional ones. The objective of this paper is to study aerodynamic study of blended wing body layout.
The presentation was prepared for an Technical Paper Presentation competition. It contains basic conceptual explanations pertaining to the BWB concept.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
Free eBook - Websites For B2 B Technogy CompaniesKim Walowsky
A complete and cost-effective web design, build and maintenance service designed to meet the specific needs of high-tech companies operating in B2B markets
Artificial intelligence (AI) is everywhere, promising self-driving cars, medical breakthroughs, and new ways of working. But how do you separate hype from reality? How can your company apply AI to solve real business problems?
Here’s what AI learnings your business should keep in mind for 2017.
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.
Fluid-Structure Interaction Over an Aircraft WingIJERDJOURNAL
ABSTRACT:- Aircraft is a brilliant man-made structure which helps us to fly over the world. At the same time, aircraft is a complex structure to be checked and maintained for the aero elasticity due to aerodynamic properties. In this paper, the fluid-structure interaction problem in super critical NASA SC(2)-0412 airfoil is discussed. The main aim of this project is to find the best performance and deformation limit of the wing on different Mach numbers. This project is completely done by numerical methods of designing the wing using CATIA and flow properties in Computational Fluid Dynamics (CFD) method. Finally, the structural analysis for deformation is analysed in ANSYS. The analytical approach of fluid-structure interaction over an Aircraft wing is complex.
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.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
Exploiting Artificial Intelligence for Empowering Researchers and Faculty, In...Dr. Vinod Kumar Kanvaria
Exploiting Artificial Intelligence for Empowering Researchers and Faculty,
International FDP on Fundamentals of Research in Social Sciences
at Integral University, Lucknow, 06.06.2024
By Dr. Vinod Kumar Kanvaria
Model Attribute Check Company Auto PropertyCeline George
In Odoo, the multi-company feature allows you to manage multiple companies within a single Odoo database instance. Each company can have its own configurations while still sharing common resources such as products, customers, and suppliers.
Read| The latest issue of The Challenger is here! We are thrilled to announce that our school paper has qualified for the NATIONAL SCHOOLS PRESS CONFERENCE (NSPC) 2024. Thank you for your unwavering support and trust. Dive into the stories that made us stand out!
Acetabularia Information For Class 9 .docxvaibhavrinwa19
Acetabularia acetabulum is a single-celled green alga that in its vegetative state is morphologically differentiated into a basal rhizoid and an axially elongated stalk, which bears whorls of branching hairs. The single diploid nucleus resides in the rhizoid.
Unit 8 - Information and Communication Technology (Paper I).pdfThiyagu K
This slides describes the basic concepts of ICT, basics of Email, Emerging Technology and Digital Initiatives in Education. This presentations aligns with the UGC Paper I syllabus.
Normal Labour/ Stages of Labour/ Mechanism of LabourWasim Ak
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Francesca Gottschalk from the OECD’s Centre for Educational Research and Innovation presents at the Ask an Expert Webinar: How can education support child empowerment?
June 3, 2024 Anti-Semitism Letter Sent to MIT President Kornbluth and MIT Cor...Levi Shapiro
Letter from the Congress of the United States regarding Anti-Semitism sent June 3rd to MIT President Sally Kornbluth, MIT Corp Chair, Mark Gorenberg
Dear Dr. Kornbluth and Mr. Gorenberg,
The US House of Representatives is deeply concerned by ongoing and pervasive acts of antisemitic
harassment and intimidation at the Massachusetts Institute of Technology (MIT). Failing to act decisively to ensure a safe learning environment for all students would be a grave dereliction of your responsibilities as President of MIT and Chair of the MIT Corporation.
This Congress will not stand idly by and allow an environment hostile to Jewish students to persist. The House believes that your institution is in violation of Title VI of the Civil Rights Act, and the inability or
unwillingness to rectify this violation through action requires accountability.
Postsecondary education is a unique opportunity for students to learn and have their ideas and beliefs challenged. However, universities receiving hundreds of millions of federal funds annually have denied
students that opportunity and have been hijacked to become venues for the promotion of terrorism, antisemitic harassment and intimidation, unlawful encampments, and in some cases, assaults and riots.
The House of Representatives will not countenance the use of federal funds to indoctrinate students into hateful, antisemitic, anti-American supporters of terrorism. Investigations into campus antisemitism by the Committee on Education and the Workforce and the Committee on Ways and Means have been expanded into a Congress-wide probe across all relevant jurisdictions to address this national crisis. The undersigned Committees will conduct oversight into the use of federal funds at MIT and its learning environment under authorities granted to each Committee.
• The Committee on Education and the Workforce has been investigating your institution since December 7, 2023. The Committee has broad jurisdiction over postsecondary education, including its compliance with Title VI of the Civil Rights Act, campus safety concerns over disruptions to the learning environment, and the awarding of federal student aid under the Higher Education Act.
• The Committee on Oversight and Accountability is investigating the sources of funding and other support flowing to groups espousing pro-Hamas propaganda and engaged in antisemitic harassment and intimidation of students. The Committee on Oversight and Accountability is the principal oversight committee of the US House of Representatives and has broad authority to investigate “any matter” at “any time” under House Rule X.
• The Committee on Ways and Means has been investigating several universities since November 15, 2023, when the Committee held a hearing entitled From Ivory Towers to Dark Corners: Investigating the Nexus Between Antisemitism, Tax-Exempt Universities, and Terror Financing. The Committee followed the hearing with letters to those institutions on January 10, 202
How to Make a Field invisible in Odoo 17Celine George
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2024.06.01 Introducing a competency framework for languag learning materials ...Sandy Millin
http://sandymillin.wordpress.com/iateflwebinar2024
Published classroom materials form the basis of syllabuses, drive teacher professional development, and have a potentially huge influence on learners, teachers and education systems. All teachers also create their own materials, whether a few sentences on a blackboard, a highly-structured fully-realised online course, or anything in between. Despite this, the knowledge and skills needed to create effective language learning materials are rarely part of teacher training, and are mostly learnt by trial and error.
Knowledge and skills frameworks, generally called competency frameworks, for ELT teachers, trainers and managers have existed for a few years now. However, until I created one for my MA dissertation, there wasn’t one drawing together what we need to know and do to be able to effectively produce language learning materials.
This webinar will introduce you to my framework, highlighting the key competencies I identified from my research. It will also show how anybody involved in language teaching (any language, not just English!), teacher training, managing schools or developing language learning materials can benefit from using the framework.
2024.06.01 Introducing a competency framework for languag learning materials ...
Design your flight 2013 guru gobind singh indraprastha university-team leo (2)
1.
2. Development Phase
In the preliminary design stages, various designs were studied and analysed for
their performance in accordance with the problem statement. Design aspects
which were beneficial for one aspect of flight but harmful for some other were
weighted for pros and cons and an ultimate decision was made in order to come
up with the best possible design for the required problem statement.
The monoplane was selected even though the biplane design offers greater
strength. This was because, strength was not the paramount concern as the plane
was supposed to be light and the preliminary designs which were tested using
ANSYS software confirmed that the structure was strong enough for the
purpose. Further biplanes have inherently more drag for a given amount of lift
than monoplanes. Monoplanes are capable of higher speeds and lower energy
consumption.
Markets were surveyed for the availability of construction material as well as
the auxiliary items required to build the plane under a decent budget and of the
desired quality.
Out of the various types of batteries available, the Lithium Polymer (Li-Po)
battery was chosen even though it is more expensive. Li-Po batteries offer the
advantages of lower weight and increased capacity and power delivery.
3. Management Phase
Organization of the team
Figure1.
Various team members were given the responsibility of various aspects of the
project. They were given these responsibilities along with the authority
necessary to carry out their responsibilities. The person best suited for the
department was chosen democratically and according to their abilities. The
members in each department were also chosen according to their abilities and
keeping in mind their personal choice. Figure1 is a diagrammatic representation
of the team’s organization.
The network analysis diagram in figure 2 clearly shows the time taken in days
in order to complete a specific task. Division of work enabled the work to be
completed quickly as members of each department were able to complete their
own tasks in a short period of time as not much man power was required for any
aspect of the project
4.
5. Conceptual Design
The problem statement requires us to carry the greatest payload possible over a
specified course. There are various regulations on take-off and flight and some
restrictions on the weight. Therefore, it is imperative to design the aircraft under
such strict conditions. The greater the payload, the more power the airplane
requires which increases the size of the batteries and the motors ultimately
increasing the size of the plane and its weight as well. Therefore, by restricting
the total weight of the airplane there is also an implied restriction on the payload
that can be carried. Better design and manufacture will help us achieve a result
as close to the maximum as possible.
The NACA four-digit wing sections define the profile by
1. First digit describing maximum camber as percentage of the chord.
2. Second digit describing the distance of maximum camber from the airfoil
leading edge in tens of percents of the chord.
3. Last two digits describing maximum thickness of the airfoil as percent of
the chord.
This formula is for the shape of a NACA 00xx foil, with "xx" being replaced by
the percentage of thickness to chord.
where:
c is the chord length,
x is the position along the chord from 0 to c,
y is the half thickness at a given value of x (centerline to surface), and
t is the maximum thickness as a fraction of the chord (so 100 t gives the last
two digits in the NACA 4-digit denomination).
6. Figure (A)
Various aspects like chord, camber etc. are illustrated in figure (A).
Equation 2
where:
m is the maximum camber (100 m is the first of the four digits),
p is the location of maximum camber (10 p is the second digit in the NACA
xxxx description).
Equation 2 was used as the cambered airfoil offers a number of advantages over
the symmetrical one.
Considered formulas:
1. Ar = Wing span/Chord length
Ar is aspect ratio
2. Wing loading= weight in oz / area in ftsq.
3. Lift=1/2 .rho. v sq.. wing area.coff. of lift
4. Wing planform area= chord length . wingspan( both for upper and lower
wings added)
7. Preliminary Design
• Various components like wings, fuselage etc. were designed using PTC
wildfire 5.0 (Pro/E).
• The design is according to the norms given in the rulebook.
• The initial design was tested for operational validity using ANSYS.
• Calculations for specifications of the driving and control motors were
done using MotoCalc 8.
The usage of software to design and test a prototype eliminates the need to
construct and test the component time and again thus saving a lot of time and
money both of which can be put to better use. But, the usage of the software
does not completely eliminate the need for models.
Several 1:1 scale models were made for solving the following problems.
• Check the availability of space for components like motor, controls etc.
• Check the dimensions achieved in actual practice.
8. Figure 3
Figure 3 shows the first prototype which was constructed out of thermocol and
glue. As can be seen, it employed a biplane design which was later discarded in
favour of a monoplane design as the monoplane gave a more satisfactory result
in analysis.
9. Figure 4.
Figure 4 shows the final model that was constructed which more closely
resembles the final design of the plane
It was constructed after the monoplane was found out to be more advantageous
as compared to the biplane design as per our requirements.
10. Detail design
After a number of designs on computer softwares and the construction of
models, a design was approved; which was deemed to be the final design.
Manufacturing and fabrication of the design was approved by the team with
valid proof that the design in robust and fit to carry out its function.
WINGS
Figure 5
Figure 5 shows the final design of the wings.
11. The final wing design has the following specifications;
• Design : NACA 2417 profile
• Material Used: Balsa Wood
• Strength (kPa): 18100 for compression parallel to grain, 4600 for shear
parallel to grain, 1200 or tension perpendicular to grain.
• Justification for selection: Balsa is an ideal material for constructing an
RC plane. This is due to the fact that not only is it light but also has high
strength for its weight. Also, it does not fail easily in bending which is the
type of stress which the wings need to withstand.
Figure 6 CFD analysis of airfoil
Figure 6 shows the successful CFD analysis of the airfoil carried out on
ANSYS.
12. Figure 7 Modal analysis
Figure7 shows the modal analysis of the wing span on ANSYS. Modal analysis
uses the overall mass and stiffness of a structure to find the various periods at
which it will naturally resonate. These periods of vibration are very important to
note in dynamic systems, as it is imperative that the natural frequency does not
match the frequency of expected vibrations. If a structure's natural frequency
matches the frequency of vibration, the structure may continue to resonate and
experience structural damage.
````````
Figure 8.
13. The analysis of the landing gear is important as the landing gear must be able to
withstand the entire weight of the plane while landing. Analysis of the landing
gear in ANSYS reveals that the design is well within the safety required for
operation.
PLANE DESIGN
Figure 9 shows the isometric view of the assembled plane on PRO/E.
Figures 10 and 11 show front view and top view respectively
15. Figure 12 Motor Specifications
Figure 12 shows the result for the motors to be used as indicated by the design
software MotoCalc. Using this information the driving and control motors were
selected from the ones available in the market.
Motor: 1800rpm/V; 0.2A no-load; 0.056 Ohms.
Battery: 1800mAh @ 3 cell 11.1V; 0.0257 Ohms/cell.
Speed Control: Generic Brushless ESC; 4 controls (separate); 0.006 Ohms;
High rate.
16. Figure 13
Figure 13 shows the controller used for flying the plane. It is a 4 channel
controller. The receiver that is used along with this controller is shown in figure
14.
18. Figure 16
Figure 16 shows a micro servo motor. Servo motors are used for control
mechanisms. Their capacities in accordance with the values calculated for a
satisfactory performance.
19. Manufacturing Process
Once the design was complete and the models were analysed and the team
members were satisfied that the design is up to the mark, the manufacturing
process was started.
The wing airfoil was made of balsa and bonded together in pairs in order to give
greater strength. The manufactured wing is shown in figure 17.
Figure 17
Such intermittent construction allows us to reduce the weight of the wings and
still maintain the shape and strength required for flight. A single airfoil is of the
shape shown in figure 18.
21. Figure 19 shows the fuselage of the plane. It has been constructed out of
chloroplast and has been bonded using super glue. Super glue was selected after
carefully analyzing the pros and cons of several bonding materials available.
The pros and cons are listed in table 1. Super glue was selected as it was easily
available and was the best option for bonding several components as the entire
airplane is not made of a single substance but is a composite of several
components.
Table 1
22. Figure 20
Figure 21
Figure 20 illustrates the push rod mechanism employed to control the motion of
the airplane. Figure 21 shows specifically the aileron control. The links are
fixed in such a way that they coincide with the zero position of the motor when
in the neutral position. This enables the controller to move the controls in either
direction easily and bringing it back to the mean position is a fairly simple task.
23. CONCLUSION
A safe and reliable design approach was adapted. Extensive testing has been
done including the gliding capabilities of the models constructed and static
analysis of the model we are ready with the final design and the airplane is
approaching completion. All is left to do is the flight analysis and test the limits
of the airplane so that the plane which we put forth to compete is capable of
competing with the other teams.