Aerodynamics and Thermodynamics Assessment

1.This assessment was designed to be completed within 3 Hours under examination conditions. You are not expected to need 24 hours to complete this assessment.

2. As this is a coursework assessment there is no extra time allocated for students with a SOSN.

This is an open book assessment so you may consult your notes, textbooks and the internet.

You must not collaborate with someone else on this assessment, it should be wholly your own work. Your work will be checked for evidence of plagiarism and/or collusion using Turnitin.

This paper contains SIX questions in TWO sections: Section A and B. Answer Two questions only in each section. The first two answered questions in each section will be marked only.

As all the questions are calculation questions, no word limit is requested. Submission Guidance

1. Please hand-write/type your solutions clearly and carefully. You will need to scan or digitally photograph these solutions if you hand write, then copy and paste them all IN THE CORRECT ORDER into a single Microsoft Word document. You should label all your solutions with correct question number, such as ‘Q2 (b)’. You should include

2. You should submit your answers as a single Word document via Canvas. Indicate the questions you have answered on the first page of your document.

3. If you include graphics in your answer please embed these into the word document (e.g. a photograph of a hand-drawn graphic). The source of any copy and pasted figures should be cited. If you have embedded any scanned / photographed diagrams and graphs, then your submission file cannot exceed 100MB. Instructions for compressing images within Word can be found here.

4. Please make sure to regularly save your work and leave plenty of time to upload your work before the deadline. All late submissions will score zero.

5. No additional material outside Canvas submission is accepted.

(a) In order to keep the fluid flow similar, the law of similarity has to be followed for any wind tunnel test. Define what the law of similarity is.

(b) Define both Reynolds number and Mach number in terms of a ratio of the forces acting on an aircraft.

(c) In discussing aerodynamic force, it is necessary to understand how the dependent variables (aerodynamic force and moment) vary with the independent variables thought to be relevant. Apply dimensional analysis to aerodynamic force to demonstrate the following relationship:

Sketch the typical variation of the section drag coefficient, Cd, with the flow Mach number, M. Identify the principal features of such a representation.

(c) Identify the seven factors which determine/influence the aerodynamic forces for a finite wing of plan-form area, S

Draw a block diagram of the jet engine and show the different cycle processes on a T-s diagram.

b) If the nozzle has an exit flow velocity of 800 m/s, calculate the specific work (work per unit mass, kJ/kg) output by turbine.

c) If the nozzle has an exit flow velocity of 800 m/s, find the turbine exit pressure.

d) Under the same conditions, what pressure could an ideal compressor generate (not the 1.5MPa as mentioned in the question, but higher). Determine the exit pressure from the compressor and the pressure ratio across the ideal compressor.

Write the stoichiometric (complete) combustion equation, and calculate the stoichiometric air/fuel ratio by volume.

b) Write the actual combustion equation and determine the actual air/fuel ratio by volume.

Determine the rate of heat transfer to ethyl alcohol.

(b) For a parallel-flow single shell-and-tube arrangement, determine heat transfer surface area required and the length of the exchanger.

(c) For a counter-flow single shell-and-tube arrangement, determine heat transfer surface area required and the length of the exchanger.

(d) Discuss your findings on the length of exchanger in terms of the single shell-and-tube arrangement from above calculations in (b)-(c). Are they practical? If not, why is not? Please give your solution in words?