List of top Aerospace Engineering Questions on Compressible Flows asked in TS PGECET

In Rayleigh flow, what happens to the stagnation pressure when heat is added, regardless of whether the flow is subsonic or supersonic?
Air \((\gamma=1.4)\) flows isentropically through a convergent-divergent nozzle. At a certain section, the Mach number is \(1.0\) (at the throat). If the stagnation temperature is \(720\ \text{K}\), find the static temperature at the throat.
An aircraft is flying at an altitude where the ambient pressure is \(0.9\ \text{kPa}\) and the density is \(1226\ \text{kg/m}^3\). Calculate the velocity of sound when adiabatic index is \(1.226\).
In a diffuser, the primary purpose is to
Fanno flow is characterized by
If the critical speed of sound is \(300\ \text{m/s}\), upstream velocity across the normal shock wave is \(600\ \text{m/s}\), the downstream velocity is
If a supersonic flow (\(M=2.0\)) encounters a convex corner (expansion), what happens to the stagnation pressure?
Critical Mach number of the airfoil is
Find the isentropic compressibility of an ideal gas with an adiabatic index of \(1.4\) at a pressure of \(1\) atm.
In Rayleigh flow, what happens to the stagnation pressure when heat is added, regardless of whether the flow is subsonic or supersonic?
Air \((\gamma=1.4)\) flows isentropically through a convergent-divergent nozzle. At a certain section, the Mach number is \(1.0\) (at the throat). If the stagnation temperature is \(720\ \text{K}\), find the static temperature at the throat.
In a diffuser, the primary purpose is to
Fanno flow is characterized by
If the critical speed of sound is \(300\ \text{m/s}\), upstream velocity across the normal shock wave is \(600\ \text{m/s}\), the downstream velocity is
If a supersonic flow (\(M=2.0\)) encounters a convex corner (expansion), what happens to the stagnation pressure?
Critical Mach number of the airfoil is
Find the isentropic compressibility of an ideal gas with an adiabatic index of \(1.4\) at a pressure of \(1\) atm.
An aircraft is flying at an altitude where the ambient pressure is \(0.9\ \text{kPa}\) and the density is \(1226\ \text{kg/m}^3\). Calculate the velocity of sound when adiabatic index is \(1.226\).