This presentation explains the different design phases of aircraft and some detailed descriptions of each phase. Then, it explains the preliminary design procedure of the aircraft which consists of weight estimation, wing design, fuselage design, drag polar, maximum speed, thrust requirement and selection of engine, landing gear selection, tail surface design, and different performance calculations.
2. PHASES OF AIRPLANE DESIGN
ο§Conceptual Design
-Variety of possible aircraft configuration arrangement, size, weight
& performance that meet the design specifications are sketched.
-New ideas & problem emerge as design is investigated.
ο§Preliminary Design
-Initial stages of design
-Specialist in area of structure, landing gear ,control system will
design and analyze their portion of aircraft.
-Testing in area of aerodynamics, propulsion & stability and control
is initiated.
-One of key activity occur in it is lofting.
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3. ο§Detail Design
-Begins with actual pieces to be fabricated are designed.
-Like; Precise design of each individual rib, spar and section of
skin takes place.
-Involves in Production design.
- specialist determine how the aircraft will be fabricated
starting with the smallest & simple sub-assemblies
and building up to the final assembly process.
- Testing effort intensifies and actual structure of aircraft is
fabricated and tested.
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5. Payload of 100 passenger
Range of 2000km
Cruise altitude = 12 km
Cruise Mach no = 0.7
Cruise speed = 743 km/hr =206.53 m/s
Landing distance = 1500 m
DESIGN REQUIREMENTS
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6. ο§Crew members = 5
ο§Weight of crew members (ππ)= 5*110 = 550 kg
ο§Weight of passenger(ππ) = 100*110 = 11000 kg
ο§Empty weight ππ
ο§Weight of fuel ππ
ο§Gross weight(π0) = ππ+ππ+ππ+ππ
= ππ + ππ +
π π
π0
π0 +
π π
π0
π0
Weight Estimation
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24. Thrust Requirement
ο§
π ππΏ
π
Ο = 0.5Οπ2
πππ₯
π
π
πΆ π·0+
2πΎπ
Ο π2
max π
ο§πππΏ= 109.80KN
ο§Thrust require maximum is 109.80KN
ο§Based on the above calculations
ROLLS-ROYCE BR715/710 Turbofan
is selected.
Specification:-
β’ Thrust range = 14000lb to 21500 lb.
β’ 20% improved fuel burn
β’ Fan diameter 58 inch and a two-stage
booster driven by a three-stage LP turbine.
β’ single low emissions annular combustor with 20 burners.
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25. Landing Gear
ο§ A conventional Tricycle landing gear is chosen based on the
trend followed by similar airplanes.
Parameter Value
Wheel base (in m) 13.2
Track length (in m) 5.8
Turning radius(in m) 19.3
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27. Tail Arm
ο§The values of the tail arm are chosen based on the data
collection as:
ο§Lh = 45 % of Lf &
ο§ Lv = 42% of Lf
Lh = 0.45 x 25.02=11.259 m
Lv = 0.42 x 25.02= 10.5084m
Vh =
πβ πΏβ
ππΆ
= 0.9
Vv =
π π πΏ π
ππΆ
= .0.569
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28. Three view drawing of Boeing 737-200
Three view Drawing
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29. [1] D.P. Raymer βAircraft design: a conceptual approachβAIAAeducational Series, Fourth
edition (2006).
[2] Harris C.H. βNASA supercritical airfoils β A matrix of family- related airfoilsβ NASA
TP 2969 , March 1990
[3] Jenkinson L. R., Simpkin P. and Rhodes D. βCivil jet aircraft designβArnold,(1999).
[4]Introduction to Flight by John D.Anderson,2nd edition.
[5]Theory of wing sections by Ira. H. Abbott, Dover edition.
REFERENCES :-
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