A DC$-10$ is cruising at its assigned altitude at a Mach number of $0\mathrm{.}85.$ The outside air temperature is $232$ K $.$ At a given point on the upper surface of the wing the pressure is measured at $\backslash (20,100\backslash$mathrm$\{$~N$\}/\backslash$mathrm$\{$m$\}^\{2\}\backslash ).$ The temperature at this point is $221$ K $.$ How much lift per square meter $($referred to ambient pressure$)$ is provided by the upper surface at this point? What is the assigned pressure altitude? What is the density altitude? What is the true speed of the airplane? $($Use SI units, but also give the upper surface lift in $\backslash (\backslash$mathrm$\{$lb$\}/\backslash$mathrm$\{$ft$\}^\{2\}\backslash ).)$