High-speed aircraft use "air data computers" to compute air speed from measurement of the difference between the stagnation and static pressures. Plot, as a function of actual Mach number \(M\), for \(M=0.1\) to \(M=0.9\), the percentage error in computing the Mach number assuming incompressibility (i.e., using the Bernoulli equation), from this pressure difference. Plot the percentage error in speed, as a function of speed, of an aircraft cruising at \(12 \mathrm{~km}\) altitude, for a range of speeds corresponding to the actual Mach number ranging from \(M=0.1\) to \(M=0.9\).