JNTUK B.Tech Aerodynamics – II gives you detail information of Flight Aerodynamics – II R13 syllabus It will be help full to understand you complete curriculum of the year.
Course Objective
The main objective of the subject is to study the concept of fluid flow and its behavior in the engine parts like Nozzle. The subject estimates the performance of aircraft in presence of flow obstacles, there by one can able to minimize the number of obstacles in the flow. It also makes the student to analyze the flow over different critical bodies and He/She able to calculate the forces generate in the experimental analysis fluid on different bodies in the wind tunnel.
Tables/Codes: Isentropic Expansion, Normal Shock, Oblique Shock.
UNIT-I : One Dimensional Flows : Isentropic process for closed system/flow processes. Velocity of sound. Mach number, flow regimes. Governing equations of inviscid compressible flow. Continuity, Momentum and Energy equations in Integral and Differential form. Stagnation conditions.
Flow Through Nozzles Isentropic flow through Convergent – Divergent nozzles. Chocked flow conditions. Normal shock. Under and over expansion conditions. Flow through diffusers – wave reflections from a free boundary. Description of supersonic wind tunnels and rocket engine.
UNIT-II : Oblique Shocks And Expansion Waves: Oblique shock relations. Supersonic flow over a wedge, M relations strong and weak shock solutions / Shock polar. Regular reflection from a solid boundary. Intersections of shock wave. Expansion waves. Prandtl – Meyer Expansion.
UNIT-III : Subsonic Compressible Flow Over Airfoil : Introduction – Velocity potential equation – Transonic small perturbation equation – Prandtl-Glauert compressibility corrections – Critical Mach number – Drag divergence Mach number – Area rule – Supercritical airfoil.
UNIT-IV : Supersonic Flow : Linearized supersonic flow- Linearized supersonic flow over airfoil and wings. Shock Expansion theory. Detached shock. Axi-symmetrical flows-flow past slender bodies of revolution, conical flows-Numerical integration procedure.
UNIT-V : Hypersonic Flows : Qualitative aspects of hypersonic flow. Newtonian theory. Flat plate at an angle of attack. Hypersonic shock wave relations. Lift and drag of wings at hypersonic speeds. Recent advances in hypersonic flows and testing techniques.
UNIT-VI : Flow Measurements And Model Testing : Non dimensional parameters and II numbers Similarity of flows. Model testing in wind tunnels. Pressure, Velocity measurements – Hotwire and Laser – Doppler anemometer, Turbulence measurements. Measurement errors. Testsection speed, horizontal buoyancy, flow angularities. Force Measurements Wind Tunnel Balances Force measurements – Wind tunnel balances. Scale effects and corrections, wall interferences, induced drag and other computations/corrections.
TEXT BOOKS
- Anderson, J .D, Fundamental of Aerodynamics, Mc Graw-Hill International third edition Singapore-2001.
- Radhakrishnan, E, E., Gas Dynamics, Prentice Hall of India, 1995
REFERENCE BOOKS
- Anderson, J .D, Modern Compressible Fluid Flow, Mc Graw-Hill International Edition
- Hodge B.K & Koenig K Compressible Fluid Dynamics with Computer Application, Prentice Hall, 1995
- Clancy, L.J., Aerodynamics, Pitman, 1986, Macmillan, 1985
Course Outcomes:
- Upon completion of the course the students shall be able to:
- Identify the concept of fluid flow and its behavior in the engine parts like Nozzle.
- Estimates the performance of aircraft in presence of flow obstacles,
- Minimize the number of obstacles in the flow.
- Analyze the flow over different critical bodies
- Calculate the forces generate in the experimental analysis fluid on different bodies in the wind tunnel.
For more information about all JNTU updates please stay connected to us on FB and don’t hesitate to ask any questions in the comment.