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EG-194 Introduction to Aerospace Engineering

Assignment 1, 2023

This assignment should take the average student around 10 hours to complete to a good

standard. It is expected that six to eight hours will be required to find, read and

understand relevant material from a variety of sources. A well-written report that

adheres to the format described below will probably take between two to four hours to

write.

The assignment title is:

Discuss the advantages, disadvantages and prospects for aircraft

using fuel-cells

Notes, Format and Submission

Fuel cells, using hydrogen or ammonia as a fuel for example, work like batteries, but

they do not run down or need recharging, which is an option for future aircraft to reduce

the emissions such as CO2. For example, the company ZeroAvia conducted a 10-minute

test flight using an engine that converts hydrogen fuel into electricity to power one of

the plane's two propellers.

You are required to write a two-page paper on the topic of fuel-cell powered aircraft

that includes a technical overview of one or more designs and details of how the

design(s) address concerns such as life-circle assessment, safety, the environment or

sustainability. There is no requirement to cover all the concerns listed.

The paper should start with an introduction to the topic and briefly describe the concept

of fuel-cell-powered aircraft. Additionally at this stage whichever life-circle assessment,

safety, environmental and sustainability will play a part later in the paper should be

explained in general. The main part of the paper should use one or more examples from

current developments or research that relate to the essay topic and identify progress in

the area. With any approach, there are normally advantages and disadvantages. Authors

will usually tell you the advantages but you should also consider what the disadvantages

of the approach are (why is the approach not being used at this time?). Also, consider

how is the design addressing the area(s) of concern that you have focussed on? The

paper should conclude by drawing together the issues described and suggesting the

likely prospects for achieving the goals. A successful response to this assignment would

be a well-organised and argued case that displays an understanding of the underlying

issues related to aerospace engineering. You will have to be precise and selective with

what you include as the format instructions below limit the space you have available.

The assignment must be written in a word processing package and submitted

electronically. The MAXIMUM LENGTH is 2 pages, using 12-point Times New

Roman font and A4 paper size, all MARGINS must be at least 4 cm and single line

spacing must be used. All pages should have a header with your name on the left and

your student number on the right. The first page should have the assignment title (given

above) as the title, in bold type. Any pictures or diagrams included used must be within

the page and margin constraints given above. The length constraints mean that only a

small number of sources are likely to be cited - any references should be included on

Fig: 1

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Question 5: An aircraft climbs at an angle of 15°. The weight of the aircraft is 114 kN and its wing area is 68 m². The aircraft's drag equation is given by CD 0.035 +0.025 C. If the engines of the aircraft produce 55 kN of thrust during the climb what is the fastest equivalent airspeed the aircraft could be climbing at? The answer should have units of m s 1. =

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Evaluation and Discussion 8. Task A: A1: A2: A3: A4: A5: A4: A5: Why pressure distribution on the upper and lower surface are the same for NACA0015 airfoil at zero AOA? Why there is a difference in pressure distribution between the upper and lower surface for cases you simulated in this Task? Which sides (upper or lower surface) has higher pressure, and why? Do you see the difference in pressure (between upper and lower surface) changes with AOA? Why? Describe the pressure distribution on the upper surface by identifying the stagnation point, suction peak, and adverse pressure region. What is Cp? How do we compute the lift coefficient of the aerofoil from the Cp distribution? (15 marks)

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Question 1 2 pts Question 1: In a wind tunnel test of flow over a wing section, air enters the test section at a speed of 54 m s1 and a pressure of 942 kPa. Assuming Bernoulli's principle applies to the flow, what is the pressure at the stagnation point on the wing surface if the air density is 1.16 kg m 3? The answer should have units of kPa.

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t Figure 8.4 shows a drag polar plot of a glider, with C₁/CD and C2/C3 superimposed as func- ons of the lift coefficient. For a given weight, W, wing area, S and altitude, h (this determines the density), by selecting a range of values for angle of attack, it is possible to compute: C₁/CD, C/C, V and RD. The corre- sponding performance data are shown in Table 8.1. The glider selected for this example is a relatively poor one by modern standards. Its lowest flight path angles are high compared to those achievable with modern gliders. Trimmed lift-to-drag ratios of 40.0 to 50.0 have already been achieved, yielding descent angles as low as 1.2 degrees! Despite this, the reader is asked to verify that the approximations of Eqns (8.22) - (8.24) are quite good! The performance results of Table 8.1 are plotted in Figure 8.5. The reader is asked to check out the significance of the points labeled A, B and C in Figures 8.4 and 8.5. These very important points are discussed next.

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For a particular airfoil section the pitching moment coefficient about an axis 1/3 chordbehind the leading edge varies with the lift coefficient in the following manner: a) Find the acrodynamic center and the value of Cmac ·b) Find the relation between the position of the center of pressure and the lift coefficient;plot a curve showing the variation of the position of center of pressure with liſtcoefficient.

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