1. U3AEA04 ELEMENTS OF AERONAUTICS
Mr. SYED ALAY HASHIM
Assistant Professor
Department of Aeronautical Engineering
VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY
Chennai
INDIA

2. POWER POINT PRESENTATION
I to V
UNIT
POWER POINT PRESENTATION

3. AIRCRAFT COMPONENTS

4. TYPES OF WING Monoplane Biplane Tandem wing Triplane Quadruplane
Multiplane 
Canard wing

5. SWEEP WING

6. Leading edge extensions of various kinds

7. AIRCRAFT
HISTORICAL RECORDS

12. Introduction AEROSPACE ENGINES
Comprehend the basic components of gas turbine engines and their basic operations
Comprehend the thermodynamic processes occurring in a gas turbine engines
Comprehend the support systems associated with gas turbine engines

13. Gas Turbine Cycle Gas Turbine Cycle
Single stage Ideal gas turbine cycle
Gas Turbine Cycle
Two stage turbine cycle

14. Gas Turbine Cycle
Two stage Compressor and Turbine cycle

15. Jet Propulsion Cycle
In practical or actual cycle Entropy is not constant

16. Jet Engine Basic Components

17. Compressor Supplies high pressure air for combustion process
centrifugal flow and Axial flow
Centrifugal Compressor
Adv: simple design, good for low compression ratios (5:1), strong
Disadvantage: Difficult to stage, less efficient, high frontal area

18. Compressor Axial flow Good for high compression ratios (20:1)
Most commonly used

20. Turbine Convert the kinetic energy into expansion work
It is used to drive the compressor as well as
propeller shaft

21. Comparison of Gas Turbine and Piston Engine

22. Classification of Engine
Air Breathing Engine Non-Air Breathing Engine
(Using atm air to produced Power)
(Presents of Fuel and absents of Air
instead of Air + Oxidizer. Hypersonic vehicles, Operating Mach No : 15 to 20)
Jet Engines Reciprocating Engines
(Propulsive thrust is produced by jet)
Rocket Engine
(No moving parts)
Gas Turbine Engine Non-Gas Turbine Engine
(Available moving parts like
Compressor and Turbine)
(No moving parts)
Ramjet Scramjet Pulsejet
Turbojet Turboprop Turbofan Turbo-shaft

24. Turbojet Chemical energy is converted into mechanical energy
100% Thrust produced by Nozzle
Operating Mach No: 1 to 2
Supersonic Aircraft (1 to 5)

26. Turbofan 20 to 40% of Thrust produced by Nozzle
60 to 80% of Thrust produced by Fan
Operating Mach No: 0.4 to 0.8
High Subsonic Aircraft (0.3 to 0.8)

28. Turboprop 20 to 25% of Thrust produced by Nozzle
75 to 80% of Thrust produced by Propeller
Operating Mach No: 0.4 to 0.65
Subsonic Aircraft (0.1 to 0.8)

29. Turbo Shaft High pressure turbine is used to rotate HP & LP Compressor
Low pressure turbine is used to rotate output Shaft
No Thrust produced in the exit turbine gas

30. Turbo Shaft Kinetic energy is converted to Shaft power
100% Thrust produced by Shaft
Operating Mach No: 0.4 to 0.8
High speed Subsonic helicopter (0.3 to 0.8)

32. Pulse Jet Made up of few moving parts
Valved engines use a mechanical valve to control the flow of expanding exhaust, forcing the hot gas to go out the back of the engine through the tailpipe
Starting the engine usually requires forced air and an ignition method such as a spark plug for the fuel-air mix.
It can operate statically

33. Rocket Engines
A rocket is a machine that develops thrust by the rapid expulsion of matter
A rocket is called a launch vehicle when it is used to launch a satellite or other payload into space
Rocket engines are reaction engines
The highest exhaust velocities
It is used in missile

34. Passenger airplanes Sl. No. Description Less Moderate High 1
Specific fuel consumption
Turbofan
Turboprop
Turbojet 2
Noise Level 3
Operating Mach No 4
Take off Thrust 5
Altitude 6
Load Carrying capacity 7
Specific Impulse

35. Thrust Equation Total Thrust = Momentum Thrust + Pressure Thrust
mi=mj (mass flow rate)
Inlet pressure = Exit pressure
Thrust force is the forward motion of engine

36. Factors Affecting Thrust
PRESSURE
TEMPERATURE
DENSITY
HUMIDITY
ALTITUDE
FORWARD VELOCITY

37. Methods of Thrust Augmentation
After burning
High thrust for short duration
It is used only in take-off (or) for high climbing rates
Additional fuel is burning in the tail pipe between the turbine and exhaust nozzle
It is increased the jet velocity
Oxidizer-Fuel Mixture
Increase the mass flow rate
Evaporative cooling which produces higher pressure and higher mass flow rate
Increase the compressor pressure ratio due to reduced compressor air flow
Water and menthol or alcohol Mixture

39. After burner

40. Oxidizer-Fuel Mixture
Evaporative cooling which produces higher pressure and higher mass flow rate

41. Advantages of Gas turbine Engines
Weight reduction of 70%
Simplicity
Reduced manning requirements
Quicker response time
Faster Acceleration/deceleration
Modular replacement
Less vibrations
More economical

42. Disadvantages of Gas Turbine Engines
Many parts under high stress
High pitched noise
Needs large quantities of air
Large quantities of hot exhaust (target)
Cannot be repaired in place

43. TYPES OF FUSELAGE STRUCTURE

47. FUSELAGE DESIGN

48. WING STRUCTURE

49. Thank you