High$-$speed aircraft use $$air data computers$$ to compute air speed from Pitot$-$static tube measurements of the stagnation pressure and static pressure. $($a$)$Plot the percent error in computing the Mach number assuming incompressibility $($thus$,$ using the Bernoulli equation$)$ versus actual Mach number for Ma$=0\mathrm{.}1$to Ma$=0\mathrm{.}9.($b$)$ For an aircraft cruising at an altitude of z$=12$km$,$ plot the speed calculated assuming incompressible flow and accounting for compressibility versus actual Mach number for Ma$=0\mathrm{.}1$to Ma$=0\mathrm{.}9.$