Jawaharlal Nehru Technological University Hyderabad B.Tech III AERODYNAMICS II Previous Question Paper (November/December - 2018 - R13)

Differentiate between a compressible fluid and an incompressible fluid.

Classify the flow regimes in terms of Mach number.

Explain the meaning of stagnation state with an example.

How the velocity of flow varies in convergent and divergent ducts for subsonic and supersonic conditions?

Explain the differences between shock waves and expansion wave.

Explain Prandtl-Meyer expansion using a sketch.

What is choked flow and what are the necessary conditions for it to occur in a nozzle?

What is transonic buffeting and what are its effects?

Discuss briefly the physical aspects of conical flow.

What is Mach number independence in hypersonic flows?

Define internal energy and enthalpy. State the first law of thermodynamics and obtain the first law equation for a system undergoing an infinitesimal thermodynamic change.

Define the concept of isentropic process. Explain why this concept is important in the study of compressible flows.

Derive Bernoulli equation for compressible flow assuming the flow to be isentropic, isothermal.

Derive an expression for the Mach number of flow downstream of a normal shock, in terms of the Mach number upstream of the shock stating the assumptions made.

Derive continuity equation in integral form using control volume approach.

Derive an expression for area ratio A/A* in terms of Mach number for an isentropic flow of a perfect gas. Here A is area at any section and A* is area at the reference section.

What is an oblique shock wave and when does it occur? Give some practical situations where the oblique shocks are produced.

Explain the intersection of shocks of opposite families using a sketch.

Derive the relationship connecting the upstream Mach number, deflection angle and shock wave angle for an oblique shock wave.

Explain how shock expansion theory can be used to calculate drag for supersonic flow over a symmetrical diamond shaped airfoil at zero angle of attack using a sketch.

Derive Area-Mach number relation for isentropic subsonic-supersonic flow of a perfect gas through convergent-divergent nozzle.

Explain area rule for controlling drag rise in transonic regime of flow.

Derive Prandtl-Glauert rule relating compressible pressure coefficient to incompressible pressure coefficient using linearized subsonic flow theory.

Describe supercritical airfoil with a sketch and explain how it is useful in increasing drag-divergence Mach number.

Derive expressions for pressure coefficient, lift coefficient and drag coefficient for supersonic flow past a flat plate airfoil at an angle of attack using Ackeret linearized theory.

Explain briefly the distinguishing flow characteristics of hypersonic flows.

Discuss the flow over a supersonic blunt body with a sketch.

Derive expressions for aerodynamic coefficients for a flat plate at an angle of attack in hypersonic flow using Newtonian theory.