AE2303 AERODYNAMICS – II ANNA UNIVERSITY QUESTION BANK, QUESTION PAPER, IMPORTANT QUESTIONS 2 MARKS and 16 MARKS QUESTIONS
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UNIT I ONE DIMENSIONAL COMPRESSIBLE FLOW 10
Energy, Momentum, continuity and state equations, velocity of sound, adiabatic steady
state flow equations, Flow through convergent- divergent passage, Performance under
various back pressures.
UNIT II NORMAL, OBLIQUE SHOCKS 12
Prandtl 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 turning angle, shock polar, flow past wedges and
concave corners, strong, weak and detached shocks,
UNIT III EXPANSION WAVES, RAYLEIGH AND FANNO FLOW 10
Flow past convex corners, Expansion hodograph, Reflection and interaction of shocks
and expansion, waves. Method of Characteristics Two dimensional supersonic nozzle
contours. Rayleigh and Fanno Flow.
UNIT IV DIFFERENTIAL EQUATIONS OF MOTION FOR
STEADY COMPRESSIBLE FLOWS 7
Small perturbation potential theory, solutions for supersonic flows, Mach waves and
Mach angles, Prandtl-Glauert affine transformation relations for subsonic flows,
Linearised two dimensional supersonic flow theory, Lift, drag pitching moment and
center of pressure of supersonic profiles.
UNIT V TRANSONIC FLOW OVER WING 6
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.
TOTAL: 45 PERIODS
TEXT BOOK
1. Rathakrishnan, E., “Gas Dynamics”, Prentice Hall of India, 2003.
REFERENCES
1. Shapiro, A.H., “Dynamics and Thermodynamics of Compressible Fluid Flow”, Ronald
Press, 1982.
2. Zucrow, M.J. and Anderson, J.D., “Elements of gas dynamics”, McGraw-Hill Book
Co., New York, 1989.
3. Anderson Jr., D., – “Modern compressible flows”, McGraw-Hill Book Co., New York
1999.
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