Department of Mechanical Engineering, Unit Catalogue 2010/11 |
ME20022: Thermofluids 4 - fluid mechanics with historical perspective |
 Credits:
| 6 |
| Level:
| Intermediate |
| Period: | This unit is available in... |
| Semester 2 |
| Assessment:
| CW 15%, EX 85% |
| Supplementary Assessment: | ME20022 Re-Assessment Examination (where allowed by programme regulations) |
| Requisites:
| Before taking this unit you must take ME20015 This unit is not normally available to visiting/exchange students. |
| Description:
| Aims: To develop the student's ability to apply the principles of fluid dynamics to problems of engineering importance at high and low speeds. Learning Outcomes: After taking this unit the student should be able to: * Understand the flow over a two-dimensional aerofoil and how lift and drag are generated. * Calculate the skin friction and drag caused by boundary-layer flow over external surfaces. Understand the importance of the Reynolds number. * Calculate the pressure losses in duct/pipe networks, and understand the fundamental fluid mechanics which causes friction. * Understand the effects of compressibility on fluid flow and solve engineering problems dealing with high-speed aerodynamics. Skills: Problem solving; numeracy; working independently. Content: VISCOUS FLOWS: Introduction to effects of fluid viscosity, laminar and turbulent pipe flows, Reynolds experiment, effects of roughness, minor losses, boundary layers in zero pressure gradients, transition, effect of pressure gradient, including flow separation. COMPRESSIBLE FLOW: Mach number and speed of sound. Shock waves. Area-change. Flow through a converging-diverging nozzle. Application to rockets and aerospace engineering. BOUNDARY LAYERS: Introduction, skin-friction and pressure drag, high-lift devices for aerofoils, drag on spheres and sports balls. HISTORICAL PERSPECTIVE: History of fluid dynamics and flight in the 20th and 21st century. AEROFOIL LABORATORY: measure lift coefficient versus angle of attack for a NACA 2415 aerofoil with and without a leading edge slat. Examine aerodynamic stall and Reynolds number effects. |