Figure Q1 shows a half view of a light aircraft, with an aileron extending over the outer 50% of the wing. The aileron is extended upwards reducing the lift over this part of the wing. You are to model the half wing as a cantilever beam, with lift represented by a uniform distributed load of 1.0 kN/m acting upwards over the entire wing section, with an additional distributed load of 0.5 kN/m acting downward over the aileron section. (a) Draw a free body diagram for the wing with aileron acting as described, and calculate the reactions at the wing root. (b) Create a shear force and bending moment diagram for the wing, clearly indicating all key values. (c) Calculate the angle of rotation of the wing tip if the wing has a bending stiffness of El = 4×105 N m?. 5.0 т 2.5 m A close up of a logo Description automatically generated Figure Q1 – Half view of light aircraft showing location of aileron.
Figure Q1 shows a half view of a light aircraft, with an aileron extending over the outer 50% of the wing. The aileron is extended upwards reducing the lift over this part of the wing. You are to model the half wing as a cantilever beam, with lift represented by a uniform distributed load of 1.0 kN/m acting upwards over the entire wing section, with an additional distributed load of 0.5 kN/m acting downward over the aileron section. (a) Draw a free body diagram for the wing with aileron acting as described, and calculate the reactions at the wing root. (b) Create a shear force and bending moment diagram for the wing, clearly indicating all key values. (c) Calculate the angle of rotation of the wing tip if the wing has a bending stiffness of El = 4×105 N m?. 5.0 т 2.5 m A close up of a logo Description automatically generated Figure Q1 – Half view of light aircraft showing location of aileron.
Chapter2: Loads On Structures
Section: Chapter Questions
Problem 1P
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Transcribed Image Text:Figure Q1 shows a half view of a light aircraft, with an aileron extending over
the outer 50% of the wing. The aileron is extended upwards reducing the lift
over this part of the wing. You are to model the half wing as a cantilever
beam, with lift represented by a uniform distributed load of 1.0 kN/m acting
upwards over the entire wing section, with an additional distributed load of
0.5 kN/m acting downward over the aileron section.
(a) Draw a free body diagram for the wing with aileron acting as described,
and calculate the reactions at the wing root.
(b) Create a shear force and bending moment diagram for the wing, clearly
indicating all key values.
(c) Calculate the angle of rotation of the wing tip if the wing has a bending
stiffness of El = 4×105 N m?.
Transcribed Image Text:5.0 т
2.5 m
A close up of a logo
Description automatically generated
Figure Q1 – Half view of light aircraft showing location of aileron.
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