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2. Many different quantities in aerospace engineering depend on the temperature, pressure, and density of the atmosphere at the current altitude. The atmosphere can be modeled as a series of alternating isothermal and gradient regions. Within the gradient region, the temperature (T), pressure (p), and density (p) are defined by the following equations: T' = T, + a (h-hi) =(F) Ti = T1 where a is lapse rate for the region in oRft, R is the specific gas constant of 1716 (ft lbf) (slug* R), go is the acceleration due to gravity of 32.2 ft/s2, and h represents the geopotential altitude in ft. The subscript 1 indicates that the value of the parameter is from the base of the region. The first gradient region in the atmosphere begins at sea level (0 ft), where T-51 8.69R, p-21 16.2 lbfft, and = 0.002377 slug/ft. and ends around 36089 ft. See the document "The Standard Atmosphere" under References on Blackboard