Unit1
1. Velocity of sound
2. Steady state flow equation **
3. Performance under various back pressure
4. Continuity and state equations**
Unit 2
1.Prandti equation and Rankine Hugonoit relation**
2.Normal shock equations**
3.Hodograph and pressure tuming angle
4.Shock polar, concave corners(maybe 2 Mark)
Unit 3
1. Reflection and interaction of shocks and expansion
2.Method of Characteristics Two dimensional supersonic nozzle contours***
3.Rayleigh and Fanno Flows.**
Unit 4
1. solutions for supersonic flows, Mach waves and Mach angles**
2. Prandti-Glauert rule affine transformation relations for subsonic flows**
3.linearized two dimensional supersonic flow theory Lift, drag
Unit 5
1.Lower and upper critical Mach numbers, Lift and drag,
2. divergence, shock induced separation**
3. Characteristics of swept wings, Effects of thickness, camber
Syllabus
UNIT 1 ONE DIMENSIONAL COMPRESSIBLE FLOW
Energy, Momentum, continuity and state equations, velocity of sound, adiabatic steady state fiow equations, Flow through convergent- divergent passage, Performance under various back pressures.
UNIT II NORMAL AND OBLIQUE SHOCKS
Prandti equation and Rankine Hugonoit relation, Normal shock equations, Pitot static tube, corrections for subsonic and supersonic flows, Oblique shocks and corresponding equations, Hodograph and pressure tuming angle, shock polar, flow past wedges and concave corners, strong, weak and detached shocks
UNIT III EXPANSION WAVES AND METHOD OF CHARACTERISTICS
Flow past convex comers, Expansion hodograph, Reflection and interaction of shocks and expansion, waves. Method of Characteristics Two dimensional supersonic nozzle contours. Rayleigh and Fanno Flows.
UNIT IV DIFFERENTIAL EQUATIONS OF MOTION FOR STEADY COMPRESSIBLE FLOWS
Small perturbation potential theory, solutions for supersonic flows, Mach waves and Mach angles, Prandti-Glauert rule affine transformation relations for subsonic flows, linearized two dimensional supersonic flow theory Lift, drag, pitching moment and center of pressure of supersonic profiles.
UNIT V ULTRANSONIC FLOW OVER WING
Lower and upper critical Mach numbers, Lift and drag, divergence, shock induced separation, Characteristics of swept wings, Effects of thickness, camber and aspect ratio of wings, Transonic area rule.