MEC 6882 - Gas Dynamics

• Apply engineering principles and analyze problems dealing with compressible flow and gas dynamics
• Formulate and solve problems in one-dimensional steady compressible flow: isentropic nozzle flow, constant area flow with friction (Fanno flow), and constant area flow with heat transfer (Rayleigh flow)
• Derive the conditions for the change in pressure, density, and temperature for flow through a normal shock
• Determine the strength of oblique shock waves on wedge-shaped bodies and concave corners
• Determine the change in flow conditions through a Prandtl-Meyer expansion wave
• Compare shock expansion with linearized theory for subsonic and supersonic flow over airfoil
• Design a supersonic nozzle using the method of characteristics

• Thermodynamics: Second Law
• Fluid mechanics 

• Review of the fundamentals (laws of thermodynamics, conservation of mass, momentum and energy, entropy changes for perfect gases, stagnation properties)
• Introduction to compressible flow (sonic velocity, Mach number, stagnation relations in terms of Mach number, total pressure loss and entropy change relation, isentropic flow tables)
• Standing normal shocks
• Fanno flow and applications
• Rayleigh flow and applications
• Oblique shocks
• Prandtl-Meyer flow (including lift and drag calculations on airfoils at various angles of attack)
• Varying-area adiabatic flow (convergent-divergent nozzle, diffuser, choking)
• Supersonic nozzle experiment and Mach number calculations
• Applications of compressible flow in propulsion systems (example: ramjet engine)
• Differential conservation equations
• Moving normal shock waves
• Velocity potential equation
• Linearized flow: subsonic and supersonic
• Conical flow
• Method of characteristics
• Finite difference techniques for steady supersonic flow