### Calculate the temperature and density of the flow

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##### Reference no: EM132607844

AERODYNAMICS

Standard Atmosphere

Question 1: At 12 km in the standard atmosphere, the pressure, density, and temperature are 1.9399 x 104 N/m2, 3.1194 x 10-1 kg/m3, and 216.66 K, respectively. Using these values, calculate the standard atmospheric values of pressure, density and temperature at an altitude of 18 km, and check with the standard altitude tables.

Given:
h = 12 km; P12km = 1.9399 x 104 N/m2 ; ρ12km = 3.1194 x 10-1 kg/m3
T12km = 216.66 K; P18km = ?; ρ18km = ?; T18km = ?

Question 2: A supersonic nozzle is also a convergent-divergent duct, which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10 atm and 300 K, respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume the flow is isentropic and, of course, compressible.

Question 3: Consider a rectangular wing mounted in a low-speed subsonic wing tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has a NACA 23012 airfoil section and a chord of 0.3 m, calculate the lift, drag, and moment about the quarter chord per unit span when the airflow pressure, temperature, and velocity are 1 atm, 303 K, and 42 m/s, respectively. The angle of attack is 8°.

Some aerodynamics related questions:

1. Increasing the viscosity of a gas will _________ the temperature.

2. The condition of flight during which the main rotor is driven only by aerodynamic forces with no power from the engine is known as _________.

3. When does a shock stall occur?

4. Best described as indicated airspeed corrected for installation and instrument error.

5. Which is the ratio of water vapor actually present in the atmosphere to the amount that would be present in the air were saturated at the prevailing temperature and pressure.

6. The speed at which the airplane will stall before exceeding its design limit-load factor in turbulent conditions or when the flight controls are suddenly and fully deflected in flight.

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