JNTU B.Tech III AERODYNAMICS II Previous Question Paper (January/February-2023 - R13)

What are the limitations of first law of thermodynamics?

What do you mean by isentropic compressibility?

For a convergent nozzle, show the variation of mass flow rate for different values of p/p0.

Write the exact equation for irrotational flow over an arbitrary body.

Write a short note on wall interference and scale effects.

Explain thin shock layer and entropy layer with neat sketch.

Show the adiabatic flow behavior in straight and variable channels.

Discuss briefly about supersonic barrier. Explain how the barrier formed.

Write the boundary conditions in linearized supersonic flow.

Write the Principle of limited upstream influence in supersonic flow.

Define Internal Energy and show that internal energy is a property of the system.

Prove the equivalence of Kelvin Planck and Clausius Statements of second law of thermodynamics.

Explain entropy and disorder. Prove that entropy is a property of a system.

What is speed of sound? Derive the expression for speed of sound for perfect gas under isentropic conditions.

Derive the Mach number equation across the normal shock wave in terms upstream Mach number.

Deduce the isentropic relation between stagnation and sonic conditions for temperature, pressure and density.

The velocity of a normal shock wave moving into stagnant air (P=1.0 bar, t=170 C) is 500 m/s. If the area of cross section of duct is constant. Determine: i) Pressure ii) Temperature iii) Velocity of air iv) Stagnation temperature v) The Mach number imported upstream of the wave front.

Obtain an expression for velocity of sound on terms of specific heats and local temperature in air medium from one dimensional continuity equations.

With a neat illustration, distinguish between reflection and refraction of shock waves.

A uniform flow at M1=2.0 passes over an expansion corner with a wall inclination of 10 degrees. Find the Mach number of the flow downstream of the expansion fan.

An oblique shock wave is reflected from a solid wall. If the upstream Mach number of the incident oblique shock wave is 2.5 and the oblique shock angle is 40 degrees. Find the Mach numbers of downstream of the incident and reflected shock wave.

Define attached and detached shocks. What conditions favour detachment of shock waves in supersonic flows over solid bodies?

Derive the Prandtl-Glauret compressibility correction relations for subsonic flows.

Based on small perturbation theory, derive the linearized velocity potential equation for compressible flows.

Illustrate why a Converging-Diverging configuration is required for the acceleration of flow from subsonic to supersonic condition.

Explain with suitable sketches the effect of pressure ratio on flow in a Laval nozzle.

Use the method of characteristics explain briefly the procedure to be followed for the design of a supersonic nozzle.

Explain various Air loads over flat rectangular wings of finite span with neat sketches.

Derive the expression of Newtonian theory for Hypersonic flow.

Differentiate between the windward surface and lee surface Newtonian flow models.