flow over bicycle

Objective: clear allclose allclc %input variablesdensity= 1.225; %density of air in kg/m3coeff_drag=linspace(0.5,1.28,25) %drag coeffs for aerofoil to flat platea=1.5; %frontal area in m2v=1:25; %velocity from 1 to 25 m/s %calculationdrag_force=0.5.*coeff_drag.*density*a.*v.^2 figure();plot(v,drag_force,\'linewidth\',3)set(gca,\'Xlim\',[1…