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.
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Case 01 (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. |
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Case 02 (project groups 2 & 13) Unsteady and steady inviscid compressible flow around airfoil: 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. |
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Case 03 (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. |
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Case 04 (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. |
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Case 05 (project groups 5 & 16) Supersonic flow over a biconvex 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. |
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Case 06 (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. |
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Case 07 (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. |
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Case 08 (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. |
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Case 09 (project groups 9 & 20) Forward-facing step in a supersonic wind tunnel: 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. |
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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. |
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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. |