Aerospace Engineering > GATE 2017 > Compressible Flow
A De Laval nozzle is to be designed for an exit Mach number of 1.5. The reservoir conditions are given as P∘=1 atm (gage), T∘=20°C. γ=1.4. Assuming shock free flow in the nozzle, the exit absolute pressure (in atm) is (in three decimal places)
Correct : 0.540
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......