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AIRCRAFT DESIGN PROJECT 1 by ashisharavind

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PADUR, CHENNAI-603103

AIRCRAFT DESIGN PROJECT- I






"DESIGN OF MEDIUM RANGE 100-150 SEATER
REGIONAL JET AIRCRAFT"



PRESENTED AND COMPILED BY,
ARAVIND SASIKUMAR
ASHISH P KALAYIL
DENNY JOSEPH
BASIL MATHEW



HINDUSTAN UNIVERSITY
PADUR, CHENNAI-603103


AIRCRAFT DESIGN PROJECT - I

"DESIGN OF MEDIUM RANGE 100-150 SEATER
REGIONAL JET AIRCRAFT"




PRESENTED AND COMPILED BY,
1) ARAVIND SASIKUMAR (0900108021)
2) ASHISH P KALAYIL (0900108023)
3) BASIL MATHEW (0900108028)
4) DENNY JOSEPH (0900108036)






AIRCRAFT DESIGN PROJECT- I
AE -1315
PROJECT REPORT
REG.No:_________________________

Name of the Project:
Department : Aeronautical Engineering
Certified that this is a bonafide project done by
______________________________________________
of Aero VI-A during the academic year 2011-2012 on
"DESIGN OF MEDIUM RANGE 100-150 SEATER REGIONAL JET
AIRCRAFT"

INT.Examiner___________ Staff in Charge_________
EXT.Examiner___________

Name of the Examination :_________________________
REG:No


:_________________________

ACKNOWLEDGEMENT


We have taken efforts in this project. However, it would not have been possible
without the kind support and help of many individuals and the institution. We would like to
extend our sincere thanks to all of them.

First and foremost we would like to thank Almighty God for his kind blessing which
helped us out doing this project. We would extend our heartful and deepest thanks to
Prof.R.Asokan, HOD Aeronautical Dept: for giving us his kind and able support. At this
occasions we must emphasise that this "AIRCRAFT DESIGN PROJECT I" would have
not been possible without the highly informative and valuable guidance by our faculty
Mr.Manikandan for his guiding and correction of various documents of mine with attention
and care. He has taken pain to go through the project and make necessary corrections when
needed.

We express our thanks to the Instructor Mr. Shanmugam for extending his support,
vast knowledge and experience which has made me to do this project with ease and
perfection. We have the great pleasure in expressing our sincere whole hearted thanks to him.

Last but not least we wish to avail ourselves of this opportunity, express a sense of
gratitude, appreciations and love to our friends, our classmates, our well wishers and our
beloved parents for their manual support, strength, help and for everything in developing the
project and people who have willingly helped us out with their abilities for their kind co-
operation to the completion of our project work.












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INDEX
Serial
Topic
Page No.
No.
1
Objective
4
2
Abstract
5
3
Introduction
6
4
Comparative Data Sheet
12
5
Comparative Graphs
15
6
Mean Design Parameters
23
7
Weight Estimation
25
8
Power plant Selection
30
9
Fuel Weight Validation
35
10
Wing Selection
37
11
Airfoil Selection
53
12
Lift Estimation
66
13
Drag Estimation
74
14
Landing Gear Arrangement
83
15
Fuselage Design
87
16
Performance Characteristics
96
17
3 - View Diagram
106
18
Conclusion
109
19
Bibliography
111



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OBJECTIVE


The aim of this design project is to design a 150 seater passenger aircraft by
comparing the data and specifications of present aircrafts in this category and to calculate the
performance characteristics.The required graphs are to be plotted and diagrams have to be
included wherever needed.

The following design requirements and research studies are set for the project:


Design an aircraft that will transport 150 passengers and their baggage over a design range
of 3000 km at a cruise speed of about 870 km/h.
To provide the passengers with high levels of safety and comfort.
To operate from regional and international airports.
To use advanced and state of the art technologies in order to reduce the operating costs.
To offer a unique and competitive service to existing scheduled operations.
To assess the development potential in the primary role of the aircraft.
To produce a commercial analysis of the aircraft project.












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ABSTRACT

The Purpose of the project is to design a 100 to 150 seater intermediate to medium range
International passenger aircraft. The aircraft will possess a low wing, tricycle landing gear
and conventional tail arrangement. Such an aircraft must possess a wide body configuration
to provide the required sufficient seating capacity. It must possess turbofan engines to
provide the required amount of thrust, range and fuel economy for the operator. The aircraft
will possess two engines.





















5 | P a g e





INTRODUCTION



It has been projected that the need for a short-range mid-sized, aircraft is increasing.
The future strategy to decrease long-haul flights will increase the demand for short-haul
flights. Since passengers prefer to meet their destinations quickly, airlines will increase the
frequency of flights, which will reduce the passenger load on the aircraft. If a point-to-point
flight is not possible, passengers will prefer only a one-stop short connecting flight to their
final destination. A 150-passenger aircraft is an ideal vehicle for these situations. It is mid-
sized aircraft and has a range of 3000 nautical miles. This type of aircraft would market U.S.
domestic flights or inter-European flight routes.

An aircraft is a complex system consisting of a combination of propulsion,
aerodynamics, Structures, control, and other subsystems. Similar to other complex systems,
the development of a new aircraft is very cost significant. Traditionally, the design process of
an aircraft starts with the sizing of the aircraft via the initial estimate of its design takeoff
gross weight. This approach, however, becomes inapplicable when the design concept in
hand is revolutionary in nature as the traditional method heavily depends on making crude
estimations and approximations from the database of previously existing designs. Moreover,
the method involves too many vague assumptions that could affect the reliability of the end
product of the conceptual design stage. This situation will cause changes being made to the
design in later stages. As being investigated in the product design process from
manufacturing point of view, changes in later stages will correspond to higher added costs
compared to that incurred if changes were made in early stages .To avoid this from
happening, the knowledge of the design should be increased in the early stages as to ensure
that the generated design concept will have high compatibility with the downstream process.

In order to explore the design space, a new method of concept assessment in aircraft
design, viz, the Technology Identification, Evaluation and Selection (TIES), has been
developed at the Georgia Tech Aerospace Systems Design Laboratory (ASDL). TIES is
defined as a Comprehensive, structured, and robust methodology for decision making in the
early phases of aircraft design. This allows the designer to determine if there is a feasible
and viable design for the given requirements available within the existing level of technology.
If the design space does not exist for the current technology, TIES allows for the evaluation
of new or upcoming technologies and their impact on the design and will assess different
technology combinations. This method will enable the designer or the decision maker to
easily access and trade-off the impact of various technologies in the absence of sophisticated,
time-consuming mathematical formulations






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