7ENT1139 - Aerospace Aerodynamics - Engineering Assignment Help

Assignment Task

Learning Outcomes (from Definitive Module Document):
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.

CFD Assignment - 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 0.02 m in diameter, with a 0.01 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.

3-2: Airflow over an Aerofoil

Choose a Mach number and Angle of Attack to simulate the airflow a NACA 0012 aerofoil. Compare your simulation results with those from literature for validation.

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