CAE338 High Speed Aerodynamics Syllabus:
CAE338 High Speed Aerodynamics Syllabus – Anna University Regulation 2021
COURSE OBJECTIVES:
1. To get insight into the basic aspects of compressible flow.
2. To arrive at the shock wave and expansion wave relations.
3. To get exposure on potential equation for 2-dimensionla compressible flow.
4. To get knowledge on high speed flow over airfoils, wings and airplane configuration.
5. To gain basic knowledge on low and high speed wind tunnels.
UNIT I FUNDAMENTAL ASPECTS OF COMPRESSIBLE FLOW
Compressibility, Continuity, Momentum and energy equation for steady one dimensional flow compressible Bernoulli’s equation-Calorically perfect gas, Mach Number, Speed of sound, Area – Mach number – Velocity relation, Mach cone, Mach angle, One dimensional Isentropic flow through variable area duct, Static and Stagnation properties, Critical conditions, Characteristic Mach number, Area-Mach number relation, Maximum discharge velocity.
UNIT II SHOCK AND EXPANSION WAVES
Normal shock relations, Prandtl’s relation-Hugoniot equation, Raleigh Supersonic Pitot tube equation-Moving normal shock waves, Oblique shocks, θ-β-M relation, Shock Polar, Reflection of oblique shocks, left running and right running waves-Interaction of oblique shock waves, slip line, Rayleigh flow, Fanno flow, Expansion waves, Prandtl-Meyer expansion, Maximum turning angle, Simple and non-simple regions, operating characteristics of Nozzles, under expansion, over expansion.
UNIT III TWO DIMENSIONAL COMPRESSIBLE FLOW
Potential equation for 2-dimensional compressible flow, Linearization of potential equation, perturbation potential, Linearized Pressure Coefficient, Linearized subsonic flow, PrandtlGlauert rule, Linearized supersonic flow, Method of characteristics.
UNIT IV HIGH SPEED FLOW OVER AIRFOILS, WINGS AND AIRPLANE CONFIGURATION
Critical Mach number, Drag divergence Mach number, Shock Stall, Supercritical Airfoil Sections, Transonic area rule, Swept wing, Airfoils for supersonic flows, Lift, drag, Pitching moment and Centre of pressure for supersonic profiles, Shock expansion theory, wave drag, supersonic wings, Design considerations for supersonic aircrafts.
UNIT V CHARACTERIZATION OF HIGH SPEED FLOWS
Shock-Boundary layer interaction, Wind tunnels for transonic, Supersonic and hypersonic flows, shock tube, Gun tunnels, Supersonic flow visualization, Introduction to Hypersonic Flows.
TOTAL: 45 PERIODS
COURSE OUTCOMES:
CO1: Analyze the effect of compressibility at high-speeds and to make intelligent design decisions based on this understanding.
CO2: Analyse about shock waves and expansion waves.
CO3: Calculate 2D compressible flows.
CO4: Estimate the high speed flow over airfoils and wings.
TEXT BOOKS:
1. Anderson, J. D, Modern Compressible Flow: With Historical Perspective McGraw-Hill Education; 3rd edition, 2003.
2. Rathakrishnan. E, Gas Dynamics, Prentice-Hall of India Pvt., Ltd, 2008.
REFERENCES:
1. Oosthuizen,P.H., &Carscallen,W.E., Compressible Fluid Flow, CRC Press; 2nd edition (July 22, 2013)
2. Shapiro, A. H., Dynamics and Thermodynamics of Compressible Fluid Flow, Ronald Press, 1982.
3. Zucrow, M. J. and Anderson, J. D., Elements of Gas Dynamics, McGraw- Hill &Co., 1989.