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
A
2.95
B
0.79
C
1.18
D
0.64

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...
#67 Fill in the Blanks
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...
#112 MCQ
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...
#182 MSQ

Related Topics

compressible flow past airfoil inviscid flow thin airfoil GATE Aerospace Engineering 2014 compressible flow subsonic Mach number calculation specific heat ratio 1.4 free stream Mach number subsonic flow airfoil Mach number calculation

Unique Visitor Count

Total Unique Visitors

Loading......

Question Options

Contributed by: