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CFD Simulation of Aerospace Flows and Radiator Heat Transfer


Penalties for Late Submissions

• Late submission of any item of coursework for each day or part thereof (or for hard copy submission only, working day or part thereof) for up to five days after the published deadline, coursework relating  to modules at Levels 0, 4, 5, 6 submitted late (including deferred coursework, but with the exception of referred coursework), will have the numeric grade reduced by 10 grade points until or unless the numeric grade reaches or is 40. Where the numeric grade awarded for the assessment is less than 40, no lateness penalty will be applied.

• Late submission of referred coursework will automatically be awarded a grade of zero (0).

• Coursework (including deferred coursework) submitted later than five days (five working days in the case of hard copy submission) after the published deadline will be awarded a grade of zero (0).

• Where genuine serious adverse circumstances apply, you may apply for an extension to the hand-in date, provided the extension is requested a reasonable period in advance of the deadline.

This Assignment assesses the following module Learning Outcomes (Take these from the module DMD):

LO2: Develop a knowledge and understanding of the application of CFD to model complex flows in aerospace applications

LO4: Apply Computational Fluid Dynamics (CFD) software to simulate aircraft component flows as well as for a complete aircraft

Assignment Brief:

Marks will be awarded for a well-reasoned report, comparisons to theoretical models or experimental data and taking reasonable assumptions during simulation process. A description of these assumptions and models used in the simulations is also highly encouraged.

Submission Requirements:

Students are required to submit their work to Canvas as a WORD or PDF document. No other document type should be submitted. No exceed 20 pages. No submissions by email will be accepted.

A note to the Students:

1. For undergraduate modules, a score above 40% represent a pass performance at honours level.

2. For postgraduate modules, a score of 50% or above represents a pass mark.

3. Modules may have several components of assessment and may require a pass in all elements. For further details, please consult the relevant Module Guide or ask the Module Leader.

Write a single report including all the three parts of the assignment. Compare to the underlying theory behind the simulations and analytical or literature data. 3-1: Air Flow within an Annulus The pipe is of 0.04 m in diameter, with a 0.02 m diameter solid core which is axially aligned. Inlet velocity: uniformly distributed, with a value to ensure the flow is within the laminar regime. Air temperature: 25°C. Compare the results of the simulation to an analytical model derived from Navier-Stokes equation.

It is expected that the velocity results of the derived solution and the CFD simulation should present a profile resembling a parabola but with a bias towards one side caused by the logarithmic term. Analytical details can be found in p. 362, Fluid Mechanics, 4th edition by F. M. White.

The simulation model resembles a radiator in a small room (3 m x 3 m, two-dimensional).  The four walls can be set at a steady temperature of T1. It contains a small 0.3 m x 0.75   ‘radiator’ which is at a stable temperature of T2 and heated the room through conductingheat into air that it contacts and spread via convection flows to the rest of the room. Theradiator is located near the left wall. Please give the exact location of the radiator byyourself.

T1 and T2 are to be chosen by you, and the temperature difference should be larger than 10°C. You can also choose to set no more than three walls, out of four (ceiling, floor, twoside walls), as adiabatic. You just need to run one simulation under specific boundary conditions.


1) As the temperature in the radiator (orange colour in Fig. 2) is fixed, it is not needed to do the simulation within the radiator. Just use a model as shown in the shaded area as attached, where the black boundary has a temperature of T1, the orange boundary is with  a temperature of T2. Only one material is in the shaded domain, which is air. No material such as aluminium etc. is needed.

2) As the problem is 2D simplified from the actual 3D reality, Fig. 2 is a side view. The lower  horizontal line is floor, the upper horizontal line is ceiling, and the two vertical lines are sides of the room. The direction of gravitational force is shown in Fig. 2.

aerospace aerodynamics


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