AE3502 Aerodynamics II Syllabus:
AE3502 Aerodynamics II Syllabus – Anna University Regulation 2021
COURSE OBJECTIVES:
• To introduce the concepts of compressibility,
• To learn the theory behind the formation of shocks and expansion fans in Supersonic flows.
• To introduce the methodology of measurements in Supersonic flows.
• To get knowledge on high speed flow over air foils, wings and airplane configuration.
• To learn the concepts of Transonic flow
UNIT I ONE DIMENSIONAL COMPRESSIBLE FLOW
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 AND OBLIQUE SHOCKS
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 AND METHOD OF CHARACTERISTICS
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 Flows.
UNIT IV DIFFERENTIAL EQUATIONS OF MOTION FOR STEADY COMPRESSIBLE FLOWS
Small perturbation potential theory, solutions for supersonic flows, Mach waves and Mach angles, Prandtl-Glauert rule – affine transformation relations for subsonic flows, linearized two dimensional supersonic flow theory – Lift, drag, pitching moment and center of pressure of supersonic profiles.
UNIT V TRANSONIC FLOW OVER WING
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
COURSE OUTCOMES:
Upon completion of the course, Students will be able to
CO1: Calculate the compressible flow through a duct of varying cross section.
CO2: Use quasi one-dimensional theory to analyse compressible flow problems.
CO3: Estimate fluid properties in Rayleigh and Fanno type flows.
CO4: Estimate the properties across normal and oblique shock waves.
CO5: Understand the knowledge of various techniques and methods for solving differential equations of motion for steady compressible flows.
CO6: Predict the properties of transonic flows.
TEXT BOOKS:
1. Anderson Jr., D., – “Modern compressible flows”, McGraw-Hill Book Co., New York, 1999.
2. L.J. Clancy, “Aerodynamics” Sterling Book House, 2006
REFERENCES
1. Rathakrishnan, E., “Gas Dynamics”, 6th Edition, Prentice Hall of India, 2017.
2. Shapiro, A.H., “Dynamics and Thermodynamics of Compressible Fluid Flow”, Ronald Press, 1982.