It is determined by the altimeter and correlates to ambient pressure.

• a. Temperature Altitude
• b. Density Altitude
• c. Pressure Altitude
• d. None of the Above

What are the three equations that will be used in deriving formulas to calculate for normal shock wave properties?

• A. Mass, Momentum, & Energy Eq.
• B. Momentum, Perfect Gas, & Continuity Eq.
• C. Energy, Continuity, & Momentum Eq.
• D. Perfect Gas, Equation of State, Momentum Eq.

A shock wave that is unattached to the surface, staying ahead of the leading edge given specific conditions.

• A. Expansion Wave
• B. Oblique Shock
• C. Normal Shockwaves
• D. Bow Shock

The sum of the energies of all the molecules in a finite volume of a gas.

• A. Enthalpy
• B. Internal Energy
• C. Entropy
• D. Perfect Gas

In this flow, the density of the fluid is considered constant:

• a. Compressible flow
• b. Incompressible flow
• c. Adiabatic flow
• d. Isentropic flow

This is the angle to which a flow can turn isentropically for a given initial and final Mach number. This is also the maximum angle through which a sonic flow can be turned around in a convex corner.

• a. Mach Angle
• b. Wave Angle
• c. Prandtl Meyer Expansion Fan
• d. Prandtl Meyer Function

The specific heat ratio of a gas is 1.83. Assuming that the air is at standard condition, what is the cp and cv of the gas in English units?

• a. 4783.47 ft. lb/slug.R and 3067.47 ft.lb/slug.R
• b. 3783.47 ft. lb/slug.R and 2067.47 ft.lb/slug.R
• c. 2783.47 ft. lb/slug.R and 3067.47 ft.lb/slug.R
• d. 2067.47 ft. lb/slug.R and 3783.47 ft.lb/slug.R

The ______ is the ratio of inertial forces to viscous forces within a fluid which is subjected to relative internal movement due to different fluid viscosities. It is also a dimensionless quantity that is used to determine the flow pattern while flowing through a pipe.

• a. Mach Number
• b. Reynolds Number
• c. Specific Heat Ratio
• d. Speed of Sound

A Cessna 152 is flying with a velocity of 420 ft/s at a pressure altitude of 12000 ft. Given that the Mach number is 0.6, calculate for the density of air experienced by the aircraft.

• A. 1.65 x 10-3 kg/m3
• B. 5.24 x 10-3 kg/m3
• C. 3.85 x 10-3 slug/ft3
• D. 1.65 x 10-3 slug/ft3

It is the rate at which the temperature in the atmosphere falls with altitude

• a. Temperature change rate
• b. Enthalpy
• c. Gradient rate
• d. Lapse rate