Aerospace Engineering > GATE 2022 > Compressible Flow
A convergent-divergent nozzle with adiabatic walls is designed for an exit Mach number of 2.3. It is discharging air to the atmosphere under the conditions indicated in the figure.
Flow through the nozzle is inviscid, the characteristic gas constant for air is 287 J/(kg-K), and γ = 1.4. When the reservoir pressure is 25 bar (absolute), and temperature is 300 K, Prandtl-Meyer expansion waves appear at the nozzle exit as shown.
The minimum percentage change in the reservoir pressure required to eliminate the wave system at the nozzle exit under steady-state is _______ %.
Flow through the nozzle is inviscid, the characteristic gas constant for air is 287 J/(kg-K), and γ = 1.4. When the reservoir pressure is 25 bar (absolute), and temperature is 300 K, Prandtl-Meyer expansion waves appear at the nozzle exit as shown.
The minimum percentage change in the reservoir pressure required to eliminate the wave system at the nozzle exit under steady-state is _______ %.
Correct : 49 to 51 or -51 to -49
Similar Questions
Consider the following Fanno flow problem: Flow enters a constant area duct at a temperature of 273 K and a Mach number of 0.2 and eventually reaches sonic cond...
A perfect gas stored in a large reservoir exhausts into the atmosphere through a convergent duct. The reservoir pressure is Po and temperature is To. The jet em...
A convergent nozzle fed from a constant pressure, constant temperature reservoir, is discharging air to the atmosphere at 1 bar (absolute) with choked flow at t...
Total Unique Visitors
Loading......