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# Aerodynamics– II pdf Notes – AE-II pdf Notes

## Aerodynamics– II pdf Notes – AE-II pdf Notes file

Aerodynamics– II pdf Notes – AE-II pdf Notes – AE-II 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:

• Compressibility of fluid and flow,Perfect gas,Thermodynamics Concepts,System, Surroundings,Types of systems,isolated systems, closed systems,
• open systems,Thermodynamic Equilibrium ,Steady state,Equilibrium,Thermal equilibrium,Compressibility is thus inverse of bulk modulus.
• Hence compressibility can be defined as the incurred volummetric 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,RADIAL OUT-FLOW NOZZLES,RADIAL IN-FLOW NOZZLES,
• The second major variety of annular nozzles is the radial in-flow type, exemplified by the spike shown below,Not all rocket nozzles are alike, and the shape selected usually depends on the application.
• This section discusses the basic characteristics of the major classes of nozzles used today.

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 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.