AS4103 Space Vehicle Aerodynamics Syllabus:
AS4103 Space Vehicle Aerodynamics Syllabus – Anna University PG Syllabus Regulation 2021
COURSE OBJECTIVES:
This course will enable students to
1. Gain knowledge on the basics of low speed aerodynamics
2. Learn the physics involved in compressible flows.
3. Provide enough knowledge on boundary layers and their interactions.
4. Impart knowledge on the aerodynamic characteristics of missile components.
5. Gain an idea about aerodynamic heating phenomena.
UNIT I BASICS OF INCOMPRESSIBLE FLOW
Aerodynamic forces and moments – Centre of pressure – Aerodynamic centre – Continuity equation – Momentum equation – Stream function – Potential function – Elementary flows – Flow over cylinder, sphere and cones – Kutta Joukowski theorem– Kutta Joukowski Transformations and its applications.
UNIT II COMPRESSIBLE FLOWS
Compressibility – Speed of sound – Normal shock – Oblique shock – Expansion fan – Shock Expansion Theory – Unsteady shock waves – Fanno flow – Rayleigh flow – Wave drag- Crocco’s Theorem – Method of characteristics.
UNIT III BOUNDARY LAYER THEORY
Laminar boundary layer – Turbulent boundary layer – Prandtle mixing length theory, Velocity distribution loss – Skin friction drag estimation – Shock wave-boundary layer interactions – Thermal Boundary Layer – Exact and Approximate solutions to thermal Boundary Layer flows.
UNIT IV AERODYNAMIC CHARACTERISTICS OF MISSILES
Airframe components of missiles – Forebody shapes – Prediction of component characteristics – Wing planform for missiles Delta wing – Vortex break down – Compressibility effect on delta wing – Wing-body interference effects – Transonic and Supersonic drag reduction methods – Fin drag – Body drag.
UNIT V AERODYNAMIC HEATING
Heat transfer process – Basic parameters in aerodynamic heating – Reference temperature method – Aerodynamic heating on conical surfaces – Variable entropy effects – Heat transfer across junctures – Non isothermal wall effects – Swept shock interactions – Application of methodology in practical missile design.
TOTAL: 45 PERIODS
COURSE OUTCOMES:
At the end of the course, students will
CO1: Have through knowledge on the concepts of incompressible aerodynamics.
CO2: Be able to analyse practical problems involving Fanno and Rayleigh flow and also flow affecting phenomena.
CO3: Have knowledge on the concepts of laminar and turbulent boundary layer flows and their interaction with shock waves and thermal effects.
CO4: Able to demonstrate and analyse different configurations of missiles and their characteristics.
CO5: Be able to design efficient re-entry vehicles by solving the problem of aerodynamic heating.
REFERENCES:
1. Anderson, JD, “Fundamentals of Aerodynamics”, McGraw-Hill Book Co, 6th edition 2017.
2. Chin SS, “Missile Configuration Design”, Mc GrawHill, 1961.
3. Hermann Schlichting, “Boundary Layer Theory”, Springer, 9th edition, 2017.
4. Michael Mendenhall, “Tactical Missile Aerodynamics: Prediction Methodology, Progress in Astronautics and Aeronautics”, 1992.
5. Nielson, JackN, Stever, Gutford, “Missile Aerodynamics”, McGraw Hill, 1960.
6. Anderson, JD, “Modern Compressible Flows”, McGraw-Hill Book Co, 2010