JNTUK B.Tech Advanced Computational Aerodynamics gives you detail information of Advanced Computational Aerodynamics 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 aspects related to aircraft design and analysis. The method of estimation of size of aircraft parts, visualization and drawing of aerodynamic shapes and efficient internal layouts. The subject also considers different phases of aircraft design process when it overcomes high velocity fluid.
UNIT – I : Panel Methods: Introduction to panel method, Basic aspects of uniform source and vortex flows, Source panel method – Non-lifting flows over arbitrary two-dimensional bodies.
Vortex Panel Method : Vortex panel method – Lifting flows over arbitrary two-dimensional bodies.
UNIT – II : Method Of Characteristics: Introduction to numerical techniques for steady supersonic flows, Philosophy of method of characteristics.
Determination of characteristic lines – Two-dimensional irrotational flow. Determination of the compatibility equationand unit processes. Regions of influence and Domains of dependence.
Applications Of Method Of Characteristics:Supersonic nozzle design using method of characteristics – Description of Mc Cormack’s predictors – Corrector techniques.
UNIT – III : Transonic Relaxation Method: Theoretical aspects of transonic flows, Small Perturbation flows – Transonic small perturbation equations – Central and Backward difference schemes, Shock capturing vs. shock fitting techniques: Conservation vs. non conservation forms of governing equations, Line relaxation techniques.
UNIT – IV : Boundary Layer Equation: Introduction to boundary layer equations and their solutions. Description of the boundary layer equations. Transformation of boundary layer equations and the numerical solution method. Choice of discretization model and the generalized Crank- Nicholson Scheme. Discretization of boundary layer equations and illustration of solutions of a tridiagonal system of linear algebraic equations.
UNIT – V : Time Dependent Methods – I : Stability of Solution, Explicit time dependent methods – Euler, Backward Euler, One step trapezoidal, Backward differencing, methods, Leap Frog method.
UNIT – VI : Time Dependent Methods – II : Description of Lax-Wendroff Scheme and Mac Cormack’s two-step predictor – Corrector method. Description of time split methods and Approximate factorization schemes.
TEXT BOOKS
- John .D. Anderson “ Computational Fluid Dynamics”, McGraw Hill
- Anderson, Dale A., John C. Tanhill and Richard H.P Letcher, “Computational Fluid Mechanics and Heat transfer”, McGraw Hill, New York 1984, Volumes I & II.
REFERENCE BOOKS
- Hoffmann, K.A: Computational Fluid Dynamics for Engineers, Engineering Education System, Austin, Tex., 1989
- Kreyszig, E., Advanced Engineering Mathematics, Wiley, New York
- Introduction to Computational Fluid Dynamics, Chow CY, John Wiley, 1979
- Bose, T.K., Computation Fluid Dynamics, Wiley Eastern Ltd., 1988.
- Chow, C.Y., Introduction to Computational Fluid Dynamics, John Wiley, 1979.
- Hirsch, A.A., Introduction to Computational Fluid dynamics, Mcgraw Hill, 1989.
- Fletcher, Computational Fluid Dynamics, Vol I & II, Springer Verlag, 1993.
- Patankar, S.V., Numerical heat Transfer and Fluid Flow. Hemispher Publishing Corporation, 1992
Course Outcomes
- Describe the aspects related to aircraft design and analysis.
- Understands the method of estimation of size of aircraft parts, visualization and drawing of aerodynamic shapes and efficient internal layouts.
- Identify different phases of aircraft design process when it overcomes high velocity fluid.
- Apply Grid Generation techniques, Elliptic Grid Generator to solve prolems with high accuracy.
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