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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