Assignments

Computer Assignments
Assignment 1 One-dimensional compressible flow with heat addition and friction: a list of problems should be solved numerically using the Chalmers-developed html-based tool CFLOW.
Assignment 2 Two-dimensional flow past a symmetrical diamond wedge airfoil: numerical simulations done using the commercial CFD solver STAR-CCM+.
Assignment 3 Quasi-one-dimensional flow and unsteady wave motion: a list of problems should be solved numerically using the Chalmers-developed html-based tool CFLOW.
The Compressible Flow Project
In addition to the assignments listed above, there is a quite extensive project course element in the course that spans over all eight course weeks. The outline of the project is given in short below.

  1. Chose one of seven available cases to study (listed below)
  2. Do a literature survey for your specific case
  3. Write a literature survey report
  4. Do two-dimensional flow simulations for your case using the commercial CFD solver STAR-CCM+
  5. Write a technical report describing your case and your results
  6. Present your results in an oral presentation session in the end of the course
A more detailed instructions can be found here

Case 1 (project groups 1 & 12)

Inviscid flow through engine intake:
The flow field inside a supersonic engine intake (SR-71 Blackbird) will be calculated both analytically and numerically. The flow is assumed to be steady and two-dimensional.

Case 2 (project groups 2 & 13)

Unsteady and steady inviscid compressible flow around airfoil:
The unsteady flow developing around an airfoil after an impulsive start will be simulated numerically. The solution should (after some time) converge towards a steady-state flow condition. The flow is assumed to be two-dimensional. In addition, a supercritical airfoil is investigated and results are compared.

Case 3 (project groups 3 & 14)

Inviscid compressible under-expanded nozzle flow:
The steady state flow in and outside of a convergent nozzle including possible shocks downstream of the nozzle will be calculated numerically. The flow is assumed to be steady, two-dimensional, and axisymmetric.

Case 4 (project groups 4 & 15)

Inviscid compressible over-expanded nozzle flow:
The steady state flow in and outside of a convergent-divergent nozzle including possible shocks inside and downstream of the nozzle will be calculated numerically. The flow is assumed to be steady, two-dimensional, and axisymmetric.

Case 5 (project groups 5 & 16)

Supersonic flow over a bi-convex airfoil:
The supersonic flow over a bi-convex airfoil is investigated both numerically and analytically. The numerical predictions are compared with the analytical solution and available experimental data.

Case 6 (project groups 6 & 17)

Inviscid supersonic flow over a 2D compression/expansion ramp:
The supersonic flow over a compression/expansion ramp is investigated both numerically and analytically. The numerical predictions are compared with the analytical solution. The detached shock limit is investigated.

Case 7 (project groups 7 & 18)

Supersonic flow over a gradual 2D compression ramp:
The supersonic flow over a gradual compression ramp is analyzed numerically. Both inviscid and viscous simulations are done and results are compared.

Case 8 (project groups 8 & 19)

Supersonic flow over a cylinder:
The unsteady supersonic inviscid flow over a cylinder in a wind tunnel is investigated. The flow includes features such as moving shocks and expansions.

Case 9 (project groups 9 & 20)

Forward-facing step in a supersonic windtunnel:
The unsteady supersonic inviscid flow over a forward-facing step in a wind tunnel is investigated. The flow includes features such as moving shocks and expansions.

Case 10 (project groups 10 & 21)

SCRAMJET engine intake:
Steady-state flow for a schematic representation of an engine intake for a SCRAMJET engine is investigated numerically. The flow field that arise as high-supersonic flow enters the engine intake is very complex and includes several shock/expansion systems.

Case 11 (project groups 11 & 22)

Shock diffraction over a 90 degree corner:
Shock diffraction is a phenomenon that occurs when a moving shock reaches a sudden expansion. This is simulated numerically by setting up a shock-tube problem with an open end.