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Structural Behavior of Aircraft Wing Component Using NACA Aerofoil Profile

Coursework Tasks  

Part A  

You are required to attend the practical session to obtain the results from the laboratory session.  

1. The tutor will introduce the activities of the laboratory session using the laboratory manual.

2. Report your activities and findings as part of your Assignment. guide, this could be around 2 to 3 pages or Maximum word count shouldn’t exceed 500 Words.

You may want to include the following (sections) in your report:
Results and Discussion 

Part B  

The Airbus A300 aircraft is being used widely in the transports sector. Designs of aeroplanes depend on their wings for flight. The wing of an aeroplane is one of the most important and complicated elements in the design of an aeroplane. A wing is a type of fin with a surface that produces aerodynamic force for flight through the atmosphere. When a force acts on a body, the latter will generate these forces by the relative movement of the air compared to the plane. The first one is the lift and the latter is drag.  The lift force is directed upwards and is acting perpendicular to the displacement of the wing and the drag force is exerted in the direction opposed to the displacement of the plane. In this conventional type of wing two Aluminium alloys (AA2024 and AA7075) are widely used because of its versatility. Nevertheless, the catastrophe of an aeroplane structural part can have disastrous penalties, with consequential damage to lifecycle and the aeroplane. The exploration of the structural behavior of the aircraft wing component will provide an understanding of the different failure modes. 

Create a profile of a NACA aerofoil using the link provided (

a) Examine the point load ranging from 100 N to 5100 N with an increment of 500 N, at end of the wing. The wing is made of aluminium. Justify your answers.

b) Compare the point load solution with a theoretical solution for all the cases examined in Part (a). 

c) Inspect the effects of different materials such as Aluminium alloy, Titanium alloy, Steel and graphene (on aluminium alloy) for a velocity range of 40 m/s to 90 m/s with an increment of 10 m/s. Justify your answers.

d) Examine the leading edge or front spar twisting effect (moments) of 100 Nm to 5100 Nm with an increment of 500 Nm. Justify your answers

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