## Aerospace Propulsion- I pdf Notes – ASP-I pdf Notes file

Aerospace Propulsion- I pdf Notes – ASP-I pdf Notes – ASP-I pdf Notes file to download are listed below please check it –

Note :- These notes are according to the R09 Syllabus book of JNTU.In R13 and R15,8-units of R09 syllabus are combined into 5-units in R13 and R15 syllabus. If you have any doubts please refer to the JNTU Syllabus Book.

**Unit-1:**

- Introduction to Propulsion,Performance Parameters ,Propulsion is a systems endeavor ,Integral Momentum Theorem , Application of the Momentum Equation to an Aircraft Engine ,
- Overall Efficiency,Thermal and Propulsive Efficiency,Implications of propulsive efficiency for engine design ,Other expressions for efficiency.

**Unit-2:**

- Integral Momentum Theorem,Application of the Integral Momentum Equation to Rockets,Application of the Momentum Equation to an Aircraft Engine ,
- We can learn a great deal about the overall behavior of propulsion systems using the integral form of the momentum equation. The equation is the same as that used in fluid mechanics.

**Unit-3:**

- Efficiencies of A/C Engines,Overall Efficiency, Thermal and Propulsive Efficiency ,Implications of propulsive efficiency for engine design ,Other expressions for efficiency,
- Trends in thermal and propulsive efficiency ,In the first lecture we arrived at general expressions that related the thrust of a propulsion system to the net changes in momentum, pressure forces, etc.

**Unit-4:**

- Aircraft Performance,Vehicle Drag ,Power Required,Aircraft Range, the Breguet Range Equation,Aircraft Endurance ,
- Climbing Flight,In this lecture we will make the connections between aircraft performance and propulsion system performance,
- For a vehicle in steady, level flight, the thrust force is equal to the drag force, and lift is equal to weight.

**Unit-5:**

- Rocket Performance,Thrust and Specific Impulse for Rockets ,The Rocket Equation,During the Fall semester thermodynamics
- lectures we used the steady flow energy equation to relate the exhaust velocity of a rocket motor to the conditions in the combustion chamber and the exit pressure .

**Unit-6:**

- Rocket Nozzles: Connection of Flow to Geometry,Thrust in Terms of Nozzle Geometry,We have considered the overall performance of a rocket and seen that is directly dependent on the exit velocity of the propellant. Further,
- we have used the steady flow energy equation to determine the exhaust velocity using the combustion chamber conditions and the nozzle exit pressure.

**Unit-7:**

- Production of Thrust with a Propeller,. Application of the Integral Momentum Theorem to Propellers ,Actuator Disk Theory, Dimensional Analysis,
- Typical propeller performance ,We will now use dimensional analysis to arrive at a few important parameters for the design and choice of a propeller.
- Dimensional analysis leads to a number of coefficients which are useful for presenting performance data for propellers.

**Unit-8:**

- Ideal Cycle Analysis of Aircraft Gas Turbine Engines,In thermodynamics we represented a gas turbine engine using a Brayton cycle,
- as shown in Figure 8.1, and derived expressions for efficiency and work as functions of the temperature at various points in the cycle.

**Unit-9:**

- Energy Exchange with Moving Blades,The Euler Turbine Equation , Multistage Axial Compressors ,Velocity Triangles for an Axial Compressor Stage ,
- Velocity Triangles for an Axial Flow Turbine Stage ,The appropriate velocity triangles are shown in Figure 9.9, where again the axial velocity was assumed to be constant for purposes of illustration.