Gasdynamics Syllabus  
Course Objectives, Policies, and Grading
12.31.21
Course Calendar — Weekly Schedule
1.  Introduction and review of fundamental physical concepts; examples of compressibility effects happening around us; laws of thermodynamics.
2.  Speed of sound, bulk modulus, Mach number; conservation of mass, momentum and energy in quasi-1D flow.
3.  Stagnation pressure and temperature; subsonic and supersonic regimes in quasi-1D flow; choking at the throat. Assignment #1.
4.  Force exerted by flow on structure due to change in momentum; nozzle efficiency; Mach angle. Assignment #2.
5.  Normal steady shock waves; Rankine-Hugoniot relations; perfect gas relations across a shock; shock tunnel; supersonic pitot tubes. Assignment #3.
6.  Reflected unsteady shockwaves; supersonic diffusers; shock stability in converging and diverging ducts. Assignment #4.
7.  Design of supersonic diffusers and supersonic wind tunnels; mass spill in supersonic diffusers; choking of diffusers; shock swallowing. Design problem set #1.
8.  Example problems in preparation for the midterm quiz. Midterm quiz.
9.  1D compressible frictional flow (Fanno line flow).
10.  Supersonic and subsonic compressible flow in pipes and constant-area ducts with friction; normal shockwaves in frictional flow; Assignment #5.
11.  1D compressible flow with heat addition (Rayleigh flow). Assignment #6.
12.  2D steady oblique shocks; derivation of oblique shock relations; weak and strong oblique shocks in supersonic inlets; maximum flow turning angle. Assignment #7.
13.  2D steady Prandtl-Meyer expansion and compression fans; airfoils in supersonic flow; overexpanded and underexpanded nozzle flows; effect of back pressure on supersonic nozzles.
14.  Linearized potential flow; derivation of the working relation for linearized potential flow and outline of limitations; form drag of complex airfoils in supersonic flow; comparison with exact shock-expansion theory. Assignment #8.
15.  Design of 2D supersonic inlets using exact shock-expansion theory; ramjet and scramjet inlet design; Oswatitch condition. Design problem set #2.
16.  Final exam.
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