computer project

Consider an aircraft with the following lift-curve slope K1, wing aspect ratio AR, zero-lift drag coefficient wing planform area S, mass m, and efficiency factor e during flight: For your final project, you are to simulate the aircraft’s undamped phugoid motion. In this case, thrust exactly cancels drag. Assume a constant angle of attack, α, of 0.0495 rad. Using the 4th order Runge-Kutta technique, solve the equations of motion above for the horizontal and vertical components of velocity. The initial conditions are x = Vz = 0, z = 4800 m, and Vx = 210 m/s. Run your simulation from t = 0 to t = 400 seconds with Δt = 1.0 sec. Plot altitude vs. horizontal distance, altitude vs. time, and flight speed vs. time. You may choose any computer language you prefer for your code provided you are not using a commercial or other pre-written application to do the work for you (MATLAB, Mathematica, Excel, and other available software are not acceptable). The plots may be created by importing your data into any available software, including MATLAB. 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.