AE 9311 AERODYNAMICS SYLLABUS | ANNA UNIVERSITY ME AERONAUTICAL ENGINEERING 1ST SEM SYLLABUS REGULATION 2009 2011 2012-2013 BELOW IS THE ANNA UNIVERSITY FIRST SEMESTER ME AERONAUTICAL ENGINEERING DEPARTMENT SYLLABUS, TEXTBOOKS, REFERENCE BOOKS,EXAM PORTIONS,QUESTION BANK,PREVIOUS YEAR QUESTION PAPERS,MODEL QUESTION PAPERS, CLASS NOTES, IMPORTANT 2 MARKS, 8 MARKS, 16 MARKS TOPICS. IT IS APPLICABLE FOR ALL STUDENTS ADMITTED IN THE YEAR 2011 2012-2013 (ANNA UNIVERSITY CHENNAI,TRICHY,MADURAI, TIRUNELVELI,COIMBATORE), 2009 REGULATION OF ANNA UNIVERSITY CHENNAI AND STUDENTS ADMITTED IN ANNA UNIVERSITY CHENNAI DURING 2009
AE 9311 AERODYNAMICS L T P C
3 1 0 4
OBJECTIVE
To understand the behaviour of airflow over bodies with particular emphasis on airfoil
sections in the incompressible flow regime.
UNIT I INTRODUCTION TO AERODYNAMICS 15
Hot air balloon and aircrafts, Various types of airplanes, Wings and airfoils, lift and Drag,
Centre of pressure and aerodynamic centre, Coefficient of pressure, moment coefficient,
Continuity and Momentum equations, Point source and sink, doublet, Free and Forced
Vortex, Uniform parallel flow, combination of basic flows, Pressure and Velocity
distributions on bodies with and without circulation in ideal and real fluid flows, Magnus
effect
UNIT II INCOMPRESSIBLE FLOW THEORY 12
Conformal Transformation, Kutta condition, Karman – Trefftz profiles, Thin aerofoil
Theory and its applications. Vortex line, Horse shoe vortex, Biot - Savart law, lifting line
theory
UNIT III COMPRESSIBLE FLOW THEORY 13
Compressibility, Isentropic flow through nozzles, shocks and expansion waves, Rayleigh
and Fanno Flow, Potential equation for compressible flow, small perturbation theory,
Prandtl- Glauert Rule, Linearised supersonic flow, Method of characteristics
UNIT IV AIRFOILS, WINGS AND AIRPLANE CONFIGURATION IN
HIGH SPEED FLOWS 8
Critical Mach number, Drag divergence Mach number, Shock stall, super critical airfoils,
Transonic area rule, Swept wings (ASW and FSW), supersonic airfoils, wave drag, delta
wings, Design considerations for supersonic airplanes
4
UNIT V VISCOUS FLOW AND FLOW MEASUREMENTS 12
Basics of viscous flow theory – Boundary Layer – Displacement, momentum and Energy
Thickness – Laminar and Turbulent boundary layers – Boundary layer over flat plate –
Blasius Solution - Types of wind tunnels – Flow visualization processes – Measurement
of force and moments in wind tunnels.
L : 45 T : 15 - TOTAL NUMBER OF PERIODS : 60
TEXT BOOKS
1. J.D. Anderson, “Fundamentals of Aerodynamics”, McGraw-Hill Book Co., New
York, 1985.
2. Rathakrishnan.E., Gas Dynamics, Prentice Hall of India, 1995.
REFERENCES
1. Shapiro, A.H., Dynamics & Thermodynamics of Compressible Fluid Flow, Ronald
Press, 1982.
2. E.L. Houghton and N.B. Caruthers, Aerodynamics for Engineering Students,
Edward Arnold Publishers Ltd., London (First Indian Edition), 1988
3. Zucrow, M.J., and Anderson, J.D., Elements of gas dynamics McGraw-Hill Book
Co., New York, 1989.
4. W.H. Rae and A. Pope, “Low speed Wind Tunnel Testing”, John Wiley
Publications, 1984.
AE 9311 AERODYNAMICS L T P C
3 1 0 4
OBJECTIVE
To understand the behaviour of airflow over bodies with particular emphasis on airfoil
sections in the incompressible flow regime.
UNIT I INTRODUCTION TO AERODYNAMICS 15
Hot air balloon and aircrafts, Various types of airplanes, Wings and airfoils, lift and Drag,
Centre of pressure and aerodynamic centre, Coefficient of pressure, moment coefficient,
Continuity and Momentum equations, Point source and sink, doublet, Free and Forced
Vortex, Uniform parallel flow, combination of basic flows, Pressure and Velocity
distributions on bodies with and without circulation in ideal and real fluid flows, Magnus
effect
UNIT II INCOMPRESSIBLE FLOW THEORY 12
Conformal Transformation, Kutta condition, Karman – Trefftz profiles, Thin aerofoil
Theory and its applications. Vortex line, Horse shoe vortex, Biot - Savart law, lifting line
theory
UNIT III COMPRESSIBLE FLOW THEORY 13
Compressibility, Isentropic flow through nozzles, shocks and expansion waves, Rayleigh
and Fanno Flow, Potential equation for compressible flow, small perturbation theory,
Prandtl- Glauert Rule, Linearised supersonic flow, Method of characteristics
UNIT IV AIRFOILS, WINGS AND AIRPLANE CONFIGURATION IN
HIGH SPEED FLOWS 8
Critical Mach number, Drag divergence Mach number, Shock stall, super critical airfoils,
Transonic area rule, Swept wings (ASW and FSW), supersonic airfoils, wave drag, delta
wings, Design considerations for supersonic airplanes
4
UNIT V VISCOUS FLOW AND FLOW MEASUREMENTS 12
Basics of viscous flow theory – Boundary Layer – Displacement, momentum and Energy
Thickness – Laminar and Turbulent boundary layers – Boundary layer over flat plate –
Blasius Solution - Types of wind tunnels – Flow visualization processes – Measurement
of force and moments in wind tunnels.
L : 45 T : 15 - TOTAL NUMBER OF PERIODS : 60
TEXT BOOKS
1. J.D. Anderson, “Fundamentals of Aerodynamics”, McGraw-Hill Book Co., New
York, 1985.
2. Rathakrishnan.E., Gas Dynamics, Prentice Hall of India, 1995.
REFERENCES
1. Shapiro, A.H., Dynamics & Thermodynamics of Compressible Fluid Flow, Ronald
Press, 1982.
2. E.L. Houghton and N.B. Caruthers, Aerodynamics for Engineering Students,
Edward Arnold Publishers Ltd., London (First Indian Edition), 1988
3. Zucrow, M.J., and Anderson, J.D., Elements of gas dynamics McGraw-Hill Book
Co., New York, 1989.
4. W.H. Rae and A. Pope, “Low speed Wind Tunnel Testing”, John Wiley
Publications, 1984.
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