# [Pdf] #1: AE II Notes – Aerodynamics II Notes Pdf Free Download

AE II pdf notes – Here you can get lecture notes of aerodynamics II Notes Pdfwith unit wise topics. Here we have listed different units wise downloadable links of Aerodynamics II Notes Pdfwhere you can click to download respectively.

Aerodynamics II Notes Pdf – AE II Notes Pdf file to download are below please check it –

AE II Complete Notes

1st Unit Notes-Aerodynamics

2nd Unit Notes-Aerodynamics

3rd Unit Notes-Aerodynamics

4th Unit Notes-Aerodynamics

5th Unit Notes-Aerodynamics

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.

Aerodynamics II Pdf Notes – AE II Pdf Notes Topics

#### Unit-1:

• Compressibility of fluid and flow, Perfect gas, Thermodynamics Concepts, System, Surroundings,
• Types of systems, isolated systems, closed systems, open systems,
• Thermal equilibrium, Compressibility is thus inverse of bulk modulus.
• Hence compressibility can be defined as the incurred volumetric strain for unit change in pressure.

#### Unit-2:

• ROCKET NOZZLE,
• ROCKET NOZZLE PURPOSE,
• EXPANSION AREA RATIO,
• In theory, the only important parameter in rocket nozzle design is the expansion area ratio (e), or the ratio of exit area (A exit) to throat area (A throat), Fixing all other variables (primarily the chamber pressure), there exists only one such ratio that optimizes overall system performance for a given altitude (or ambient pressure). However, a rocket typically does not travel at only one altitude.

#### Unit-3:

• NOZZLE SHAPES,
• NOZZLE COMPARISONS,
• CONICAL NOZZLE,
• BELL NOZZLE,
• ANNULAR NOZZLES,

#### Unit-4:

• Adiabatic flow in variable area channels- nozzles, diffusers,Governing Equations ,
• Effect of Area and Velocity Variation on Flow Properties, Mass flow rate,
• Stagnation Condition, Back Pressure, Choked Flow,
• Over Expanded and Under Expanded flows in the nozzle.

#### Unit-5:

• Sound Barrier,Supercritical airfoil,
• Swept Wing, Second-order equation for transonic flows, Whitcomb’s Area Rule,
• Application of transonic Aircraft ,
• As mentioned above, even though modern airliners typically fly at about M = .85, the flow over the wings is transonic or supersonic.