You will learn in Aircraft Stability and Control that the
equations of motion of the aircraft can be written as:

&nbsp;

<img width="160" alt="" height="57">

&nbsp;

 where z is altitude and x is
the horizontal distance travelled.&nbsp; Other
parameters in the equations are:

&nbsp;

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; Vx
= horizontal velocity&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; T = thrust

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; Vz
= vertical velocity&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; D = drag

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; m =
aircraft mass&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; g = gravity

&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; L =
lift&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; g = flight path angle

&nbsp;

Lift, drag, and flight path
angle are determined by:

&nbsp;

<img width="67" alt="" height="72">&nbsp;

where Vx and Vz
are components of flight speed <img width="17" alt="" height="19">&nbsp;in the x and z directions.

Note that: 

<img width="67" alt="" height="23">&nbsp;

&nbsp;

In
Equation (8), assume that r, CL, and CD can be computed using

&nbsp;

<img width="159" alt="" height="66">&nbsp;

where
z is in meters.

&nbsp;

Consider
an aircraft with the following lift-curve slope K1, wing aspect ratio AR, zero-lift drag coefficient <img width="24" alt="" height="19">wing planform area S,
mass m, and efficiency factor e during flight:

&nbsp;

<img width="136" alt="" height="69">&nbsp;

&nbsp;

 For
your project, you are to simulate the aircraft’s undamped phugoid motion.&nbsp; In this case, thrust exactly cancels
drag.&nbsp; Assume a constant angle of attack,
a, of 0.0495
rad.&nbsp; Using the 4th‑order
Runge-Kutta technique, solve the equations of motion above for the horizontal
and vertical components of velocity.&nbsp; The
initial conditions are x = Vz &nbsp;=&nbsp;0, z = 4800 m, and Vx&nbsp;=&nbsp;210&nbsp;m/s.&nbsp; Run your simulation from t = 0 to t = 400 seconds
with Dt = 1.0 sec.

&nbsp;

Plot
altitude vs. horizontal distance, altitude
vs. time, and flight speed vs. time. 














The
plots may be created by importing your data into any available software,
including MATLAB.&nbsp; While working in small
groups to set up the problem and determine how to solve it is acceptable, all
code must be original work.&nbsp;&nbsp; 














the
plots, and numeric values for Vx,
Vz, x, and z only for time
steps 0, 5, 10, 15, …, 400, all out to exactly 2 decimal places for each time
step using all proper formatting techniques for tabulated data.&nbsp; &nbsp;&nbsp;

I need experinced lancer in Fortran language to develop a project

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