Aerospace Engineering > GATE 2011 > Compressible Flow
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. The Prandtl-Meyer function, v,
is given as a function of Mach number, M, as
Assume air to be calorically perfect with γ=1.4. The Mach number, M2, downstream of the
expansion corner is approximately
288 K around a sharp expansion corner (θ=20o) as shown below. The Prandtl-Meyer function, v,
is given as a function of Mach number, M, as
expansion corner is approximately
Correct : c
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