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Stress and Vibration Analysis of
an F-16 Fighting Falcon Wing
Kevin Escapule
Fauad Ali Shoukat
Derek Kramer
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Analysis of an F-16 Wing using
ANSYS 5.7
Maximum and minimum stress was
calculated on the wing for three cases. (free
wing, wing loaded by fuel tank, and wing
fully-loaded by armaments and fuel tank).
Vibration was also measured on the wing
for each version such as the no-load wing,the fuel tank-loaded wing, and the fully-
loaded wing.
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Loads applied on the wing.
Following are the loads applied on the
wing.
1. Sidewinder (AIM-9)
2. AMRAAM (AIM-120)
3. MAVERICK (AGM-65)4. 370 gal external fuel tank.
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Sidewinder (AIM-9)
The AIM-9 was
loaded on the wing tip.
The weight of theAIM-9 was 200 lbs.
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AMRAAM (AIM-120)
The AIM-120 was
positioned 23.21
inches from thewingtip next to the
AIM-9.
The weight of the
AMRAAM AIM-120
was found as 335 lbs.
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MAVERICK(AGM-65)
The AGM-65 was
placed at 48.75 inches
from the wingtip. There was a cluster of
three AGM-65s used,
so the total weight was
calculated as 1392 lbs
each missile being 464
lbs.
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External Fuel Tank
A 370-gallon external
fuel tank was
introduced at theposition of97.5 inches
from the wingtip.
An external fuel tank
with a weight of fuel
of 1850 lbs was
measured as a total of
2400 lbs.
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Dimensions of wing of F-16
The wing of the F-16 was 130 inches long,
100 inches wide with the angle of sweep of
400 at the leading edge. The wing tip lengthwas 25 inches.
The wing had a thickness to chord ratio of
4%.
The thickness was then 4 inches.
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Model of wing in ANSYS
Solid 92 was used as
an element type.
The wing was freemeshed volume.
The pressure on the
top of the wing was
1.85 psi and 3.75 psi
was on the bottom of
the wing.
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Stress on the wing of F-16.
The maximum and minimum stress was
calculated on the wing with no loads, with a
fuel tank, and with fuel tank andarmaments.
Two views were used to measure the
stresses, which are the isometric view andthe front view.
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Isometric view of stress on wing.
(No Loads)
This is the isometric
view of stress on wing
with no loads on it. The minimum stress
was found at the wing
tip of 2.174psi, and
the maximum stress
was found at wing root
as 5580psi.
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Front view of stress on wing
The front view ofstress on wing with no
loads gives us thebetter picture of howthe stress is distributedacross the wing. Aswe go towards thewingtip the stressdecreases to minimumstress.
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Isometric view of stress on wing.
(370-gal fuel tank)
This isometric view of
stress on wing with
external fuel tank gave us
the minimum stress of
2.119psi, which was
found at the wingtip, and
the maximum stress of
4888psi at wing root,which was shown by the
red area.
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Front view of stress on wing
This is the front view of
distribution of stress on
the wing. It was noted that
in the position that the
external fuel tank was
placed, the wing had the
maximum average stress
which is shown by theyellow and orange areas.
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Isometric view of stress on fully loaded
wing. (fuel tank + armaments)
The isometric view ofstress on the fully
loaded (fuel tank andarmaments) winggives us the minimumstress of 1.287psi atthe wingtip, and themaximum stress wasfound at the wing rootas 3709psi.
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Front view of stress on wing
This front view of stressdistribution across thisfully loaded wing shows
us that the stress is higherat the position where theMAVERICK and FUELTANK (total=3792 lbs)were placed. However, at
the wingtip the stress isminimum where thesidewinder of only 200lbwas placed.
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Vibration on the wing of an F-16
The videos of vibration on wing with no
loads, with fuel tank, and fully loaded (fuel
tank + armaments) were recorded.
The frequency of (0-1000)Hz was used to
calculate the vibration.
No natural frequency of over 6 Hertz was
observed on any of the three wing versions.
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Vibration on wing. (No Load)
This animation gives
us the vibration on the
no-load wing.
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Vibration on wing.(Fuel tank)
This animation gives
us the vibration on the
wing with the 370-gallon of external fuel
tank.
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Vibration on fully loaded wing.
(Fuel tank + Armaments)
This animation gives
us the vibration on the
fully loaded wing(370-gallon fuel tank
and armaments).
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Conclusion
Better understanding
Engineering Process
Incorporating ANSYS
Overall Process
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