Develop an understanding of the capability, scope and limitations of the different mathematical, experimental and computational tools that can be used in the aerodynamic field.

LO1 Demonstrate a comprehensive understanding of key aerodynamic principles and their interaction with related engineering disciplines such as automotive and aerospace

LO2 Develop an understanding of the capability, scope and limitations of the different mathematical, experimental and computational tools that can be used in the aerodynamic field

LO3 Use fundamental mathematical, experimental and CFD methods to undertake aerodynamic design and analysis of key engineering structures.

LO4 Conduct appropriate research and investigations to generate innovative aerodynamic design for engineering vehicle and mechanical components with improved aerodynamic efficiency.

Task 2: External flow around a wing

A model wing that can be used for aerospace applications is placed in a test section of a wind tunnel where the pressure, temperature and Mach number of the flow are 1.03 bar, 300 K, and 0.11, respectively. The wing has NACA 0015 aerofoil and a chord length of 61.5 mm. The size of the computational domain is shown in Figure Q2 and the coordinates of the aerofoil surface are provided in Tablel.