Advanced Gas Dynamics

Instructor: Dr. Rinku Mukherjee, Department of Applied Mechanics, IIT Madras.

This course introduces the concepts of the primary differences between an incompressible flow and a compressible flow. It draws the connection between compressible flow and speed of sound, Mach Number and thermodynamics. It then builds on the governing equations to derive the commonly known equations and tackles both 2D and 3D problems. The physical concept of shocks and the resulting changes in the thermodynamic properties of a fluid form a major part of this course. The course concentrates primarily on the understanding of the physical concepts of compressible flow and keeps a reference to various numerical methods for solving the governing equations to a minimum.

Mod-01 Lec-01 Lecture-01-Introduction to Gas Dynamics & Review of Basic Thermodynamics.
Mod-01 Lec-02 Lecture-02-Review of Basic Thermodynamics Continued.
Mod-01 Lec-03 An introduction to Normal Shocks.
Mod-01 Lec-04 Lecture-04-The Mach Number and Compressible Flow.
Mod-01 Lec-05 Lecture-05-The relation of physical properties across a normal shock.
Mod-01 Lec-06 Lecture-06-Normal Shock in a duct: Throat and Reservoir conditions.
Mod-01 Lec-07 Lecture-07-Example Problems in Normal Shocks.
Mod-01 Lec-08 Lecture-08-An introduction to Oblique Shocks.
Mod-01 Lec-09 The relation of physical properties across an oblique shock.
Mod-01 Lec-10 Lecture-10-Example Problems in Oblique Shocks.
Mod-01 Lec-11 Lecture-11-Pressure - Deflection relationship of Shocks.
Mod-01 Lec-12 Lecture-12-An introduction to Expansion waves.
Mod-01 Lec-13 Lecture-13-Area - Mach Relationship.
Mod-01 Lec-14 Lecture-14-Unsteady Shock Waves: The Shock Tube.
Mod-01 Lec-15 Lecture-15-The Shock Tube: Propagating Normal Shock and its reflection from end wall.
Mod-01 Lec-16 Lecture-16-A review of wave propagation.
Mod-01 Lec-17 Lecture-17-Wave propagation: Small Perturbation Theory.
Mod-01 Lec-18 Lecture-18-Finite Wave Theory: An introduction to the Method of Characteristics.
Mod-01 Lec-19 Lecture-19-The Shock Tube: Propagating Expansion Fan.
Mod-01 Lec-20 Lecture-20-The Method of Characteristics.
Mod-01 Lec-21 Lecture-21-Application of The Method of Characteristics:.
Mod-01 Lec-22 Lecture-22-Application of The Method of Characteristics:.
Mod-01 Lec-23 Lecture-23-Flow over a Wavy wall: Formulation using Perturbation Theory.
Mod-01 Lec-24 Lecture-24-Subsonic Flow over a Wavy wall.
Mod-01 Lec-25 Lecture-25-Supersonic Flow over a Wavy wall.
Mod-01 Lec-26 Lecture-26-Supersonic Flow past a 3D Cone: Axisymmetric/Quasi 2D Flow.
Mod-01 Lec-27 Lecture-27-Quasi 2D Flow - I.
Mod-01 Lec-28 Lecture-28-Quasi 2D Flow - II.
Mod-01 Lec-29 Similarity Rules and Transformed Coordinate System.
Mod-01 Lec-30 Lecture-30-Critical Mach Number and Thin Airfoil Theory.
Mod-01 Lec-31 Lecture-31-Example Problem using Thin Airfoil Theory.
Mod-01 Lec-32 Lecture-32-Example Problems - 1.
Mod-01 Lec-33 Lecture-33-Example Problems - 2.
Mod-01 Lec-34 Lecture-34-Example Problems - 3.
Mod-01 Lec-35 Lecture-35-Supersonic Flow past a 3D Cone at an angle of attack.
Mod-01 Lec-36 Lecture-36-Supersonic Flow past a 3D Cone at an angle of attack:.
Mod-01 Lec-37 Lecture-37-Supersonic Flow past a 3D Cone at an angle of attack:.
Mod-01 Lec-38 Supersonic Flow past a 3D Cone at an angle of attack: Governing Equations.
Mod-01 Lec-39 Supersonic Flow past a 3D Cone at an angle of attack: Numerical Procedure.
Mod-01 Lec-40 Supersonic Flow past a 3D Bluff Body at an angle of attack.