Aerospace Engineering > GATE 2012 > Compressible Flow
The Mach angle for a flow at Mach 2.0 is
Correct : a
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Consider the inviscid, adiabatic flow of air at free stream conditions, M1=2 p1=1 atm and T1=288 K around a sharp expansion corner (θ=20o) as shown below....
Consider the inviscid, adiabatic flow of air at free stream conditions, M1=2 p1=1 atm and T1=288 K around a sharp expansion corner (θ=20o) as shown below....
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