Trending: Anna University 8th Sem Results April 2014 May/June 2014 Time Table/ Internal Marks Calculate CGPA Online SSLC Results 2014 12th Result 2014

Test Footer 1

Sunday, August 5, 2012

AE2303 AERODYNAMICS – II SYLLABUS | ANNA UNIVERSITY BE AERONAUTICAL ENGINEERING 5TH SEMESTER SYLLABUS REGULATION 2008 2011 2012-2013

Latest: TNEA 2014 Engineering Application Status, Counselling Date, Rank List
AE2303 AERODYNAMICS – II SYLLABUS | ANNA UNIVERSITY BE AERONAUTICAL ENGINEERING 5TH SEMESTER SYLLABUS REGULATION 2008 2011 2012-2013 BELOW IS THE ANNA UNIVERSITY FIFTH SEMESTER BE AERONAUTICAL ENGINEERING DEPARTMENT SYLLABUS IT IS APPLICABLE FOR ALL STUDENTS ADMITTED IN THE YEAR 2011 2012-2013 (ANNA UNIVERSITY CHENNAI,TRICHY,MADURAI,TIRUNELVELI,COIMBATORE), 2008 REGULATION OF ANNA UNIVERSITY CHENNAI AND STUDENTS ADMITTED IN ANNA UNIVERSITY CHENNAI DURING 2009


AE2303 AERODYNAMICS – II L T P C
3 0 0 3
OBJECTIVE
To understand the behaviour of airflow both internal and external in compressible flow
regime with particular emphasis on supersonic flows.
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
44
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.

No comments:

Post a Comment

Any doubt ??? Just throw it Here...