a$,$ b$)$:

$KC{l}_L^2.$ Ignore Reynolds all engine power at an altitude of h$.$ It has a drag polar that can be represented by $C_0=C_{0p}+$

Weight: W

Planform surface area: S range in descent. Explain why this is the case. You can leave your answer in symbolic form.

b$.$ To maintain the condition in part a$,$ what will happen to the glide angle and velocity as the aircraft decreases in altitude? $($are they greater than, less than, or unchanged? explain; you don't have to calculate anything$)$