MTech Aerodynamics syllabus for 1 Sem 2020 scheme 20MAE12

Basics of Aerodynamics:

Properties of fluids, Characteristics of Atmosphere, Type of fluid flows, Generation of Lift, Drag and Moment, Incompressible flows over airfoils, calculation of lift and drag from measured pressure distribution, Streamlined and bluff-body, Reynolds number and Mach number, Conservation law of mass and momentum, Euler and Bernoulli’s equations, pitot-tube measurement of airspeed. Pressure coefficient. Streamlines, path lines and streak lines. Angular velocity, vorticity, circulation Stream function, velocity potential and their relationship. Governing equation for irrotational and incompressible fluid flow.

Aerodynamics of airfoils and wings:

Airfoil nomenclature and classification, Low speed aerodynamic characteristics of symmetric and cambered airfoils, Centre of pressure, aerodynamic centre and aerodynamic moment, Concept of point vortex, line vortex and vortex sheet, Kutta condition, Kelvins circulation theorem and starting vortex, Classical thin airfoil theory and symmetric airfoil. Finite wing nomenclature. Incompressible flow over wing, vortex filament, bound vortex, horse shoe vortex, downwash, induce angle of attack and drag. Type of drag.Biot-Savart law and Helmholtzs vortex theorem. Prandtls lifting line theory and limitations. Elliptic lift distributions, expression for induced angle of attack and induce drag. Two dimensional and three dimensional wings lift curve slope and effect of aspect ratio. High lift devices.

High speed Aerodynamics:

Fundamentals of thermodynamic concepts, conservation of energy. Speed of sound, Mach wave and Mach angle. Normal shock wave, Oblique shock wave, Expansion fan, Prandtl-Meyer expansion. Family of shocks. Flow through convergent divergent nozzle. Hodograph and pressure turning angle. RankineHugoniot relation.

Compressible flow over airfoil:

Full velocity potential equation. Small perturbation theory. Linearized velocity potential equation and boundary conditions. Pressure coefficient for small perturbation. Prandtl- Glauret compressibility correction. Critical Mach number, Drag Divergence Mach Number, Sound barrier. Transonic area rule, supercritical airfoil, swept wing and delta wing.

One dimensional flow through constant area duct:

Fanno flow and fanno line, Rayleigh flow and Rayleigh line. Method of characteristics and its application. Flow past Wedge and cone.

Course outcomes:

At the end of the course the student will be able to:

1. Solve aerodynamic problems related to pressure distribution and pressure coefficients

2. Demonstrate knowledge of compressible flows to solve one dimensional flows through constant area ducts

3. Solve problems related to normal and oblique shock waves

Question paper pattern:

The SEE question paper will be set for 100 marks and the marks scored will be proportionately reduced to 60.

• The question paper will have ten full questions carrying equal marks.
• Each full question is for 20 marks.
• There will be two full questions (with a maximum of four sub questions) from each module.
• Each full question will have sub question covering all the topics under a module.
• The students will have to answer five full questions, selecting one full question from each module.

Textbook/ Textbooks

1 Fundamentals of Aerodynamics John D. Anderson McGraw-Hill publication 5 th edition and 2010

2 Modern compressible flow John D. Anderson McGraw-Hill publication 3 rd edition and 2002

Reference Books

1 Aerodynamics for Engineering students E L Houghton and P W Carpenter Edward Arnold publication 7 th edition and 2016

2 Fundamentals of compressible flow Yahya, S M. New Age International 5 th edition and 2016

3 Introduction to flight John D. Anderson McGraw-Hill publication 6th Edition And 2008