Semester 6

COURSE OBJECTIVES

 To discuss the concepts of compressible and Incompressible fluids.

 To understand Mach number variation on area ratio.

 To impart in depth knowledge on the flow characteristics through constant area duct.

UNIT 1 FUNDAMENTALS OF COMPRESSIBLE FLUID FLOW 9 Hrs.

Concept of compressible flow, Energy and momentum equations, various regions of flow, fluid velocity, stagnation state, velocity of sound, critical states, Mach number, critical mach number, Crocco number, types of waves, mach cone, mach angle, effect of mach number on compressibility.

UNIT 2 FLOW THROUGH VARIABLE AREA DUCTS 9 Hrs.

Isentropic flow through variable area duct, T-S and h-s diagrams for nozzle and diffuser flows, area ratio as a function of Mach number, Mass flow rate through nozzles and diffusers, effect of friction in flow through nozzles.

UNIT 3 FANNO FLOW AND RAYLEIGH FLOW 9 Hrs.

Flow in constant area duct with friction - Fanno curves, and Fanno Flow equations, variation of flow properties, variation of Mach number with duct length. Flow in constant area duct with heat transfer, Rayleigh line and Rayleigh flow equations, variation of flow properties, maximum heat transfer.

UNIT 4 NORMAL SHOCK AND OBLIQUE SHOCKS 9 Hrs.

Governing equations, variation of flow parameters, static pressure, static temperature, density, stagnation pressure, entropy across normal shock and oblique shocks. Normal shocks - stationary and moving, applications. Prandtl Meyer equation, impossibility of shock in sub-sonic flows, flow in convergent and divergent nozzles with shock, Flows with oblique shock.

UNIT 5 JET AND SPACE PROPULSION 9 Hrs.

Aircraft propulsion, types and working of jet engines - energy transfer in jet engines, thrust, thrust power, propulsive and overall efficiencies, thrust augmentations in turbo jet engines, ram jet and pulse jet engines. Rocket propulsion, types of rocket engines, Liquid and solid fuel rocket engines, Introduction to Electrical and Nuclear rockets-Space Flights, Orbital and escape velocity.

COURSE OUTCOMES

On completion of the course, students will be able to

CO1 - Recall the fundamental concepts of compressible fluid flow.

CO2 - Demonstrate the significance of mach number on compressibility.

CO3 - Differentiate isothermal flow and isentropic flow.

CO4 - Apply the concept of normal shocks to different turbo machines.

CO5 - Estimate the heat transfer in flow through constant area ducts.

CO6 - Calculate the propulsive power in jet engines.

COURSE OBJECTIVES