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PRELIMINARY DESIGN OF A REGIONAL PASSINGER AIRCRAFT Team: G.S.MAHARSHI 11521A2111 B.SRIKANTH 11521A2103 Y.V.KRISHNA REDDY 11521A2123

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Page 1: priliminary design of aircraft

PRELIMINARY DESIGN OF A REGIONAL PASSINGER AIRCRAFT

Team:

G.S.MAHARSHI 11521A2111

B.SRIKANTH 11521A2103

Y.V.KRISHNA REDDY 11521A2123

Page 2: priliminary design of aircraft

COMMERCIAL TRANSPORT JETs: REGIONAL CLASS

The regional transport airplanes are currently in considerable demand and many airplane companies are engaged in their design. These airplanes could be propelled by a turbo-prop engine or a turbofan engine. The later would, have a shorter duration of flight. However, a turboprop engined airplane is more economical than the turbofan powered airplane as the range is short and payload is considerble lower than that of large commercial jets.

The examples of such airplanes are:ATR-72-200,ATR-72-500, De Havilland Dash 8- Q300,AIRBUS A320,EMBRAER 190/95 etc…

Fig: Regional Jet Aircraft Powered by Turboprop Engines

Page 3: priliminary design of aircraft

Aircraft design approach:

The design of an aircraft starts with a innovative idea or some set of requirments.The aircraft design process has split-up as

Requirments(or)idea

Conceptual design

Preliminary design

Detail design

• Estimate aircraft maximum take-off weight • Determine wing area and engine thrust (or power)

• approximate three-view of the aircraft that represents the aircraft configuration

• Finely detailed aircraft design

Page 4: priliminary design of aircraft

MAIN STRUCTURAL COMPONENTS OF AN FIXED WING AIRCRAFT:

Wing

Fuselage

Empennage

Fig:wings Fig:fuselage Fig:empennage

Page 5: priliminary design of aircraft

WING:

The wing may be considered as the most important component of an aircraft, since a fixed-wing aircraft is not able to fly without it.The wing geometry and its features will influencing all other aircraft components. The primary function of the wing is to generate sufficient lift force or simply lift (L) while generate minimum drag, and minimum pitching moment. These design goals must be collectively satisfied throughout all flight operations

Figure:Aerodynamic characteristics of a wing

(a) Cl vs α (b) Cl vs Cd (c) Cmc/4 vs α

Page 6: priliminary design of aircraft

During the wing design process, eighteen parameters must be determined. They are as follows: Wing reference (or planform) area (SW or Sref or S)

Number of the wings

Vertical position relative to the fuselage (high, mid, or low wing)

Horizontal position relative to the fuselage

Cross section (or airfoil)

Aspect ratio (AR)

Taper ratio

Tip chord (Ct)

Root chord (Cr)

Mean Aerodynamic Chord (MAC or C)

Span (b)

Twist angle (or washout)

Sweep angle

Dihedral angle

Incidence (iw)

High lifting devices such as flap

Aileron

Other aspects

Page 7: priliminary design of aircraft

Fuselage:

The primary purpose of the fuselage is to house the payload. In transport airplanes the payload includes the passangers, their luggage and cargo. In military airplanes it is the ammunition and /or special equipment. In addition to the payload, the fuselageaccommodatesFuel,landing gear,Systems like airconditioning,hydraulic,electrical,pneumatic,electronic,emergency oxygen, pressurization and auxilliary power unit.

Requirements:

STRUCTURAL:

•Skin carries cabin pressure (tension) and shear loads

•Longitudinal stringers carry the longitudinal tension and compression loads

•Circumferential frames maintain the fuselage shape and redistribute loads into the skin, and bulkheads carry concentrated loads.

MATERIAL:

•Strength, Young's modulus, fatigue initiation, fatigue crack growth, fracture toughness and corrosion are all important, but fracturetoughness is often the limiting design consideration.

Page 8: priliminary design of aircraft

Fig:Typical Segments of a Passenger Airplane Fuselage

Page 9: priliminary design of aircraft

Figure:Fuselage And Its Structural Components Of An Aircraft

Page 10: priliminary design of aircraft

Empennage:

The empennage, commonly called the tail assembly of the airplane. Its main purpose is to give stability to the aircraft. The tail in a conventional aircraft has often two components horizontal tail and vertical tail and carries two primary functions:

1. Trim (longitudinal and directional)

2. Stability (longitudinal and directional)

Since two conventional control surfaces (i.e. elevator and rudder) are indeed parts of the tails to implement control, it is proper to add the following item as the third function of tails:

3. Control (longitudinal and directional)

In general, tail is designed based on the trim requirements, but later revised based on stability and control requirements.

Page 11: priliminary design of aircraft

The following are the tail parameters which need to be determined during the design process:

1. Tail configuration

2. Horizontal tail horizontal location with respect to fuselage (aft tail or canard)

Horizontal tail

3. Planform area (Sh)

4. Tail arm (lh)

5. Airfoil section

6. Aspect ratio (ARh)

7. Taper ratio (h)

8. Tip chord (Ch_tip)

9. Root chord (Ch_root)

10. Mean Aerodynamic Chord (MACh or Ch)

11. Span (bh)

12. Sweep angle (ht)

13. Dihedral angle (ht)

14. Tail installation

15. Incidence (ih)

Vertical tail

16. Planform area (Sv)

17. Tail arm (lv)

18. Airfoil section

19. Aspect ratio (ARv)

20. Taper ratio (v)

21. Tip chord (Ct_v)

22. Root chord (Cr_v)

23. Mean Aerodynamic Chord (MACv or Cv)

24. Span (bv)

25. Sweep angle (v)

26. Dihedral angle (v)

27. Incidence (iv)

Page 12: priliminary design of aircraft

Figure:Empennage of an airplane

Page 13: priliminary design of aircraft
Page 14: priliminary design of aircraft

THANK YOU