Problem 2 (30%): The Northrop Grumman RQ-4 Global Hawk is an unmanned surveillance aircraft capable of flying at altitudes up to 60,000 ft. NASA 4801 For the purposes of this problem, assume this aircraft is in a steady-level cruise configuration with the following properties: W = 15,000 lb S = 600 ft CL=0.5 = 4.1 ft For the purposes of this assignment, assume the ISA model for the atmosphere during a standard day. Based on the weight, reference area, and lift coefficient data provided, develop a program to calculate and plot the following as a function of altitude, from standard sea-level conditions to an altitude of 60,000 ft. Alongside these plots, also provide the numerical values of the following for standard sea-level conditions (h = 0), tropopause (h = 36,000 ft), and the aircraft service ceiling (h=60,000 ft): a) The aircraft airspeed (velocity) in steady, level cruise b) The aircraft Mach number produced by the airspeed from part a. c) The chord-based Reynolds number produced in steady-level cruise.