JNTUH B.Tech 3rd Year 1 sem Aeronautical Engineering R13 (3-1) Aerodynamics – II R13 syllabus.

JNTUH B.Tech 3rd year (3-1) Aerodynamics – II gives you detail information of Aerodynamics – II R13 syllabus It will be help full to understand you complete curriculum of the year.

Aim

• The Student will learn about vaired pheonomena involving compressible flows.HE/She will learn to do elementry calculations using Normal Shock tables,Oblique shock charts,parndtl-Meyer  Funtion tables as a Preparation toward desgin of high speed aircrafts and high speed wind tunnels.

Tables and charts required to be Supplied to candidates for reference during examination

• Tables:
• 1.Isentropic Flow Properites, 2. Normal Shock Properites, 3. Prandtl-Meyer Funtion and Math Angle, 4. One Dimensional Flow With Heat Addition, 5. One Dimensional Flow With Friction, 6. Properites of INternational Standrad atmosphere and Chart: 7. Oblique Shock Properites.

UNIT-I

Thermodynamics in Fluid Motion  Definition of compressibility of flow, measure, flow regimes.Review of theromodynamics-concept of equilibrium, Thermodymic systems, Variables of state, The first law of thermodynamics, Reversible & irreversible processes, Perfect gases, internal energy and enthalpy, specific heats,Adiabatic reversible process, Relations for Thermally & Calorically perfect gas, First law applied to irreversible processes, The throttling process or Joule- Thompson process (considered most inportant for application to fluid mechanics), Entropy and second law, Entropy change relations, isentropic
relations.

UNIT-II

One Dimensional Flows  One dimsensional approximation, continuity equation for 1-D flows, Energy equation- incorporation of kinetic energy in Joule Thomposn Process, Reservoir conditions, 1-D momentum equation for inviscid flow, Bernoulli equation for compressible flow, Mach number, 1-D area- velocity relation, Convergent- divergent Channel & throat, Relations between satgaation pressure/density and Mach number, Local reservoir and autual reservoir, Sonic variblies and reservoir varibles, Di9fferent forms of energy equation, Constant area duct as a special case of 1-D flow,, Continuity and momeutum equations for constant area ducts, Experimental flow visualization of a bluff body in supersonic flow and picture of a normal Shock- constant area ducts formed by streamlines entering and leaving perpendicular to the shock. Normal shock waves: basic equations, relations across a normal shock,calculation of normal shock wave properties, measurements of airspeed in subsonic and supersonic flows.Entory rise across normal shockand its relation to pressure rise,. Numerical exercises with normal shock tables.

UNIT-III

Oblique Shock and Expansion Waves  Oblique shock relations,Supersonic flow over wedges withb attached shock,large wedge angle and shock detachment, Oblique shock charts: strong shock and weak shock boundary,pressure,density and entropy rise,Oblique shock of vanishing strength and mach wave,mach angle and mach line,supersonic compression by turning,smooth nearly isentropic turn,Numerical excercise with oblique shock charts, Regular reflection from solid wall, pressure deflection diagram,phenemenlogical description of shock wave-boundary layer interaction at the wall, intersection of shocks, Mach reflection and slip stream. Numerical exercises with shock reflectionand shock intersection, detached shock wave infront of bluff 2-D body– variation of its strength starting from normal shock, strong oblique shock,weak oblique shock to Mach waves,shock waves in front of a three dimensional body (phenomenological description only)

Supersonic expansion by turning, Prandtl-meyer function & expansion fan, Shock expansion theory-application to supersonic airfoils. Supersonic flows– over a flat plate at an angle of attack, over a diamond airfoils at a angle of attack, determination of slip stream angle, wave drag and lift, Numerical exercises with Prandtl-Meyer Function Tables. Numerical exercises determination shock-expansion-slipstream configuration & force calculation on airfoils.

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TEXT BOOKS

• Liepmann, H. W., and  Roshko, A., Elenents of Gas Dynamics, John Wiley,  1957.
• Bertin, J.J., Aerodynamics for Engineers, fourth  edn., Indian reprint, Pearson Education, 2004, ISBN:  8-1-297-0486-2.
• Rathakrishanan  E.,  Has Dynamics, Prentice- Hall of  india.
• Anderson,  J.D., Modern  compressible  Flow with  Historical Perspective, third  edn., McGraw-Hill, 2003, ISBN: 0-07-112161-7.

REFERENCES

•  McCormick, B.W., Aerodynamics, Aeronautics & Flight Mechanics, second  edn., John wiley,  1995, ISBN: 0-471-57506-2.
• Shapirol A.H., The Dynamics and Themodynamics of Compressible Fluid Flow, Vols. I and II, John Wiley, 1953.
•  Landau, L.D., & Lifshitz, E.M., Fuild Mechanics, 2nd edn., Course of Theoritical Physics, Vol. 6, Maxwell Macmillan International Edition, Pergamon, 1989, ISBN: 0-02-946234-7.

Outcome:

• Students will be able to prepare the design of high speed aircrafts and high speed wind tunnels.

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