Im given the answers just cant get to the correct answers Q5

Problem 5. 12 points] An altimeter set for sea-level standard pressure indicates an altitude of 30,000 ft. If the outside ambient temperature is 25°F, find the air density and the density altitude. Problem 6. [2 points] Consider an airplane flying at some real, geometric altitude. The outside (ambient) pressure and temperature are 0.65x105 N/m2 and 225 K, respectively. Calculate the pressure and density altitudes at which this airplane is flying.

Solution

Station Pressure = Sea-level Barometric Pressure - (Physical Altitude / 1000)

Station Pressure = 30.14 - (30000/1000) = 0.14 inches of Hg

Staton Pressure = 474.0944 Pa

PV=MRT/Z

M/V =PZ/RT [ Z of Air = 14 ]

density = P/RT = 474.094*14/ (8.31*241.483) = 3.314 Kg/m³

density = 6.43 * 10⁴ slug/ft³

ISA Temperature = 59 - (Pressure Altitude / 1000) * 3.6

ISA temperature = 59 - ( 30000/1000)*3.6

ISA Temperature = -49

Correction (feet) = (Actual Temperature - ISA Temperature) * 66.67

Correction = (-25 - (-49)) *66.67

correction = 1600.8

Density Altitude = Pressure Altitude + Temperature Correction.

Density Altitude = 30000+1600.08

Density Altitude =31600.08