Question
In: Mechanical Engineering
1. Find a picture on the internet that shows the underlying structure of an aircraft wing...
1. Find a picture on the internet that shows the underlying structure of an aircraft wing and discuss how it is similar to the box beam concept.
2.The box beam concept handles bending and torsional loads. Consider and discuss what structural elements we have explored so far in this course that address these loads. Hint: there are two (one for bending and one for torsion). Also, please include the following in the discussion.
Depending on the air vehicle performance requirements a wing’s thickness is different. For example, a lower speed vehicle such as a large transport aircraft (e.g., B-747) will have a thicker wing compared to a fighter aircraft. The reasons for this are beyond the scope of this course.
Consider the I-beam concept we have been exploring in this module. Discuss what happens as the wing thickness changes. For example, what is the variable in the bending equation that is effected as the wing thickness changes?
How could the allowable stress level be managed for the different wing structures (i.e., what happens to the skin thickness, which is the upper part of the box beam)?
Solutions
samet mamat answered 1 year agoRelated Solutions
Draw a sectional diagram of an aircraft wing, showing the structure of the wing and the...
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Delta Wing Aircraft Specifications (do the necessary assumptions if needed) Wing Area: 585 m2 Wing Span:...
Delta Wing Aircraft Specifications
(do the necessary assumptions if needed)
Wing Area: 585 m2
Wing Span: 32 m
Taper ratio: 0.019
Leading Edge Sweep angle: 65.57°
Wing loading: 4070 N/m2
Cruise Mach Number: 3
Cruise altitude: 22.5 km
(L/D) cruise = (L/D) max = 9
Calculate the cruising angle of attack?
Write down the cruising drag polar equation?
Using the drag polar found in (b), calculate
(CL1/2/CD) max and
corresponding Mach number maximizing
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An aircraft firm is considering three different alloys for use in the wing construction of a...
An aircraft firm is considering three different alloys for use
in the wing construction of a new airplane. Each alloy can be
produced in four different thicknesses (1 = thinnest, 4 =
thickest). Two test samples are constructed for each combination of
alloy type and thickness, then each of the 24 test samples is
subjected to a laboratory device the severely flexes it until
failure occurs. For each test sample the number of flexes before
failure is recorded, with the...
An aircraft firm is considering three different alloys for use in the wing construction of a...
An aircraft firm is considering three different alloys for use
in the wing construction of a new airplane. Each alloy can be
produced in four different thicknesses (1 = thinnest, 4 =
thickest). Two test samples are constructed for each combination of
alloy type and thickness, then each of the 24 test samples is
subjected to a laboratory device the severely flexes it until
failure occurs. For each test sample the number of flexes before
failure is recorded, with the...
A model aircraft in a wind tunnel with a wing area of 0.9 square meters and...
A model aircraft in a wind tunnel with a wing area of 0.9 square
meters and a chord of .24 meters is subject to a sea level standard
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center-of-gravity is measured as – 7.8 N m. At a different angle of
attack, the moment about the center-of-gravity is measured as 13.5
N m with a lift of 2,650 N.
(A)Calculate the value of the moment coefficient about the
aerodynamic center, and...
A wing component on an aircraft is fabricated from an aluminum alloy that has a plane...
A wing component on an aircraft is fabricated from an aluminum
alloy that has a plane strain fracture toughness of 30 MPa (m) 1/2
. It has been determined that fracture results at a stress of 120
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component and alloy,
Compute the stress level at which fracture will occur for a
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Describe the structure and function of wing coupling mechanisms in insects.
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1. Aerodynamics : (a) how to find zero lift line of a wing and airfoil?
[Aerospace Engineering]
1. Aerodynamics :
(a) how to find zero lift line of a wing and airfoil?
(b) how do we relate this with climb angle(gamma), pitch angle(theta), angle of incidence, and Angle of Attack(Alpha)
(c) why during climb Theta is not considered as Angle of attack since the aircraft moves with respect to x-axis? or is that with respect to thrust direction?
(d) then can we classify Angle of Attack to be similar with Angle of Incidence if the...
When commercial aircraft are inspected, wing cracks are reported as nonexistent, detectable, or critical. The history...
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(a) Find the probability that one has a critical crack, two have
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(b) Find the probability that at least one plane has critical
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(c) Find...
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