Question 41 of 50

What is the fundamental definition of Rayleigh flow?

Which of the following equations represents the energy balance for a control volume in Rayleigh flow?

On a Temperature-Entropy (T-s) diagram for Rayleigh flow, at what Mach number does the maximum entropy occur?

What happens to the temperature of a supersonic flow (M > 1/sqrt(k)) in a Rayleigh flow process when additional heat is applied?

For a Rayleigh flow with k=1.4, air enters a pipe at a Mach number of 0.25. The exit temperature is 400 K and the entrance temperature is 300 K. What is the approximate exit Mach number?

In Rayleigh flow, what happens to the stagnation temperature when heat is added to the flow?

What is the choking point in Rayleigh flow, and what does it signify?

For a Rayleigh flow with k=1.4, if the Mach number is 3.0, what is the ratio of the static temperature to the star temperature, T/T*?

In Example 10.2, heat is added to air until the flow is choked, with an exit temperature of 1000 K. How is the entrance stagnation temperature (T01) determined?

If air with a Mach number of 3 enters a frictionless duct with heating, and a normal shock occurs immediately at the entrance, what is the Mach number just after the shock?

What is the relationship between the temperature ratio (T2/T1) and the Mach number ratio (M2/M1) in Rayleigh flow?

For Rayleigh flow with k=1.4, if the Mach number is 0.5, what is the stagnation temperature ratio T0/T0*?

In Rayleigh flow, what happens to the static pressure as a subsonic flow (M < 1) is heated?

What is the ratio of stagnation pressures P0/P0* for a Rayleigh flow with k=1.4 at a Mach number of 2.0?

What happens to the stagnation pressure as a supersonic flow (M > 1) is heated in a Rayleigh flow process?

The equation for the pressure ratio P*/P1 in Rayleigh flow is given as (1 + k*M1^2) / (1 + k). What does P* represent?

In Example 10.1, with air entering a pipe at 3 bar and T=27C at M=0.25, what is the maximum temperature the air can reach before the temperature starts to decrease with further heating?

What is the key difference in assumptions between Rayleigh flow and Fanno flow?

For Rayleigh flow with k=1.4, calculate the pressure ratio P/P* for a Mach number of 0.70.

In a Rayleigh flow process, what happens to the density of the gas as a subsonic flow (M < 1) is heated?

What is the value of the density ratio rho*/rho for a Rayleigh flow with k=1.4 at a Mach number of 0.85?

In the momentum balance equation for Rayleigh flow, A(P1 - P2) = m_dot(V2 - V1), what does the term A(P1 - P2) represent?

If heat is added to a supersonic Rayleigh flow (M > 1), what happens to the Mach number?

What is the value of the stagnation pressure ratio P0/P0* for a Rayleigh flow with k=1.4 at Mach 0.30?

Why does the temperature decrease when heating a supersonic flow with M > 1/sqrt(k) in a Rayleigh process?

What does the temperature ratio T2/T1 become in the limit as the Mach number approaches infinity (M approaches infinity) for k=1.4?

For Rayleigh flow with k=1.4 and an inlet Mach number of 0.25, the exit pressure is 2.901 bar and the inlet pressure is 3 bar. The inlet total pressure P01 is 3.14 bar. What is the approximate exit total pressure P02?

What is the maximum heat that can be added to an air stream entering at M=3 if the flow is to remain entirely supersonic (no shock)?

According to the analysis in the chapter, is it possible for the stagnation temperature to remain constant across a normal shock wave?

What is the physical meaning of the ratio of heat released Q/m_dot in Rayleigh flow?

For a Rayleigh flow with k=1.4, what is the temperature ratio T/T* when M=1.2?

In a supersonic Rayleigh flow (M > 1), what happens to static pressure as the gas is cooled?

In the derivation of the Rayleigh line equations, the second law of thermodynamics is used to find an expression for the change in entropy. What is the resulting derivative ds/dM?

For a Rayleigh flow with k=1.4, what is the density ratio rho*/rho at M=1.6?

What is the relationship between the density ratio and velocity ratio in Rayleigh flow?

In a Rayleigh flow process, what is the stagnation temperature T0* at the choking point (M=1)?

If a flow enters a duct at M=0.34398 and T=584.6 K, and is heated until it chokes at an exit temperature of T*=1000 K, what was the total heat added per unit mass if Cp = 1.004 kJ/kgK?

In a Rayleigh flow, what happens to the static temperature as a supersonic flow (1 < M < 1/sqrt(k)) is cooled?

What is the pressure ratio P/P* for a Rayleigh flow with k=1.4 at M=2.5?

Why is the Rayleigh flow model useful in practice, despite its idealised assumption of frictionless flow?

How does the stagnation temperature ratio T0/T* relate to the static temperature ratio T/T*?

What happens to the static pressure in a supersonic Rayleigh flow (M > 1) as it is heated?

For a Rayleigh flow with k=1.4, what is the value for the density ratio rho*/rho at M=5.0?

Can a subsonic Rayleigh flow be brought to a supersonic state by heating alone?

What is the stagnation pressure ratio P0/P0* for k=1.4 at M=10.0?

What is the value of the stagnation temperature ratio T0/T0* for k=1.4 as the Mach number approaches zero?

Which property remains constant across a normal shock but changes during a Rayleigh process?

For a Rayleigh flow with k=1.4, what is the temperature ratio T/T* at M=0.10?

If a supersonic flow at M=3 is cooled in a Rayleigh process, what happens to its stagnation pressure?