Congratulations. You are hired as a structures engineer at Lockheed. Your first task is to determine if the new deluxe

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Congratulations. You are hired as a structures engineer at
Lockheed. Your first task is to determine if the new deluxe
passenger airliner shown below is stable. Range is sufficient
to cross the Pacific in a single flight.
Wing area is 150 square meters. Chordwise distance between
the wing effective elastic axis and aerodynamic center is 4
meters. Lift curve slope is 0.1/deg. The desired design
envelope (Mach number versus altitude ) is defined by the following
bounding points.
DesignEnvelopeMach = [0.1 0.3
0.8 0.8
0.4 0.3
0.2 0.13 0.1];
%
DesignEnvelopeAlt = [ 0
0.0 10000 15000 12000
10000 8000 5000
0]; % meters
Assume standard day for defining the design envelope.
Develop a MATLAB script called (divergence.m) to determine the
wing divergence boundary (altitude versus Mach) to determine if the
aircraft is stable. The script plots both the design flight
envelope boundary and the divergence boundary on a plot of altitude
on the y axis and Mach number on the x axis.
The stress engineer has proposed a wing box structure that has
400,000 N m / deg spring constant. However, the weights
engineer wants only 250,000 N m / deg to save weight. What is
your input as the aeroelasticity engineer? Who is correct,
the stress engineer or the weights engineer? How much spring
constant would you recommend to keep the aircraft safe from
divergence throughout its flight envelope? Explain.
Write a 1 page essay that documents your results, including a plot
showing your results, the weights engineer results, and the stress
engineer results.