For most gases at standard or near standard conditions, the relationshipamong pressure, density, and temperature is given by the perfect gasequation of state: p = ρRT, where R is the specific gas constant. For airat near standard conditions, R = 287 J/(kg · K) in the International System of Units and R = 1716 ft · lb/(slug · ◦R) in the English Engineering System of Units. Using the above information, consider the following two cases: a. At a given point on the wing of a Boeing 727, the pressure andtemperature of the air are 1.9 × 104 N/m2 and 203 K, respectively.Calculate the density at this point.b. At a point in the test section of a supersonic wind tunnel, the pressureand density of the air are 1058 lb/ft2 and 1.23 × 10−3 slug/ft3,respectively. Calculate the temperature at this point.
For most gases at standard or near standard conditions, the relationship
among pressure, density, and temperature is given by the perfect gas
equation of state: p = ρRT, where R is the specific gas constant. For air
at near standard conditions, R = 287 J/(kg · K) in the International System of Units and R = 1716 ft · lb/(slug · ◦R) in the English Engineering System of Units. Using the above information, consider the following two cases:
a. At a given point on the wing of a Boeing 727, the pressure and
temperature of the air are 1.9 × 104 N/m2 and 203 K, respectively.
Calculate the density at this point.
b. At a point in the test section of a supersonic wind tunnel, the pressure
and density of the air are 1058 lb/ft2 and 1.23 × 10−3 slug/ft3,
respectively. Calculate the temperature at this point.
Trending now
This is a popular solution!
Step by step
Solved in 2 steps
