ME 313 - Theory and Design of Compressible Flow Systems (3 Credit
Hours)
Course Description: Fundamentals of one-dimensional compressible flow including
nozzles, friction and heating effects, shock waves, and expansion waves. Application of
the basic theory in a design project.
Course Instructors: This course is typically taught by the following instructors:
Sample Syllabus: Here is a sample syllabus indicative
of that typically used in the course.
Pre-Requisite Skills: Students entering this course are expected to have mastered
the following skills:
- ESM 311 - Fluid Mechanics
- Compute the major and minor frictional losses for incompressible flow
- Apply one-dimensional continuity equation relating velocity, density, and
cross-sectional area.
- Apply the energy equation to compute pressure drops in piping.
- ME 215 - Thermodynamics
- Compute thermodynamic properties of ideal gases.
- Apply energy equation to steady flow processes including work and heat transfer.
Course Objectives: Students who successfully complete this course can be expected
to:
- Calculate speed of sound in an ideal gas. (a1)
- Compute changes in Mach number and thermodynamic properties based on simple area change
for one-dimensional isentropic compressible flow. (a1)
- Explain the behavior of isentropic compressible flow through a converging-diverging
nozzle for different back pressures. (a2)
- Determine occurrence and location of a normal shock in the diverging section of a
supersonic nozzle. (a2)
- Compute thermodynamic property changes across a normal shock.. (a2)
- Apply variable transformation to analyze moving shocks. (e)
- Design simple "blowdown" and continuous supersonic wind tunnels. (c)
- Design nozzles for jet and rocket propulsion applications. (c)
- Determine flow acceleration/deceleration due to wall friction for both supersonic and
subsonic flows. (e)
- Determine flow acceleration/deceleration due to heat transfer for both supersonic and
subsonic flows. (e)
Sample Examinations: Examples of Examinations given in this course can be found here.