Aerospace Engineering > GATE 2014 > Compressible Flow
For inviscid, compressible flow past a thin airfoil, shown in the figure, free-stream Mach number . Ratio of pressure at point A and p∞ 0.8 and specific heat ratio is 1.4, If the Mach number at point A is 1.0 and rest of the flow field is subsonic, the value of M∞ is
Correct : b
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......