ENGR 550 Gas Dynamics

Gas dynamics, also referred to as compressible flow and/or high-speed aerodynamics, is a subject dealing with gas flows at high enough Mach number wherein the fluid can no longer be assumed incompressible. Such flows occur in many aerospace and mechanical engineering applications ranging from external aerodynamics to internal flows for applications such as propulsion and airframe designs for jets, rockets, missiles, and many other devices. Topics within high-speed aerodynamics include supersonic flows, hypersonic flows, shock waves, expansion waves, supersonic wind tunnels, gas flows with friction, and gas flows with heat transfer.

Credits

3

Prerequisite

Consent of instructor

Offered

Fall

Outcomes

1. Students will understand basic relations of fluid mechanics and thermodynamics (continuity, momentum, energy, 2nd Law of Thermodynamics) from a control volume standpoint
2. Students will be able to apply the ideal gas assumption.
3. Students will be able use 1-D theory to understand basic wave propagation in gases and elastic media.
4. Students will be able to evaluate sound speeds of ideal gases and calculate Mach numbers.
5. Students will be able to categorize the various regimes defined by the Mach Number (subsonic, supersonic, hypersonic, etc).
6. Students will be able to utilize the concept of stagnation temperature and stagnation pressure for understanding and solving basic gas dynamics problems.
7. Students will be able to explain basic flow system behavior using T-S diagrams.
8. Students will be able to evaluate the effect of area changes on 1-D compressible flow.
9. Students will be able to determine when a flow system is choked and what regions should be subsonic, sonic, or supersonic.
10. Students will be able to analyze the flow in nozzles, diffusers, and from pressurized vessels.
11. Students will be able to design (conceptually) basic supersonic wind tunnels.
12. Students will be able to analyze flow systems containing stationary normal shock waves.
13. Students will be able to analyze flow systems containing stationary oblique shock waves.
14. Students will be able to determine the location of a stationary shock wave in a converging-diverging nozzle.
15. Students will be able to calculate the conditions within ducted systems containing moving shock waves.
16. Students will be able to evaluate the pressure and mach number changes through an expansion fan (Prandtl-Meyer flow).
17. Students will be able to apply oblique shock waves and expansion fans toward the design of supersonic airfoils.
18. Students will be able to apply oblique shock waves and expansion fans to supersonic nozzles and their exhaust streams.
19. Students will be able to perform calculations on a compressible, 1-D internal flow system with friction.
20. Students will be able to analyze compressible, 1-D internal flows with heat transfer.
21. Students will be able to sketch Rayleigh and Fanno lines on a T-S diagram.
22. Students will be able to use Look-Up tables for solving basic compressible flow problems.
23. Students will be able to make small computer/Excel/MathCAD/Matlab/ programs for solving basic relations of compressible flow using a computer and/or calculator without having to resort to Look-Up tables.