Isentropic Flow
Flow map
Nozzle area trades static pressure for velocity along the selected isentropic solution.
Static ratios versus Mach number
Mach = 2.000
Current Mach
2.000
p/p₀
0.12780
T/T₀
0.55556
ρ/ρ₀
0.23005
Mach number
2.000
Supersonic
Area ratio
1.688
A/A*, relative to the sonic throat
Pressure ratio
0.1278
p/p0 static to stagnation
Temperature ratio
0.5556
T/T0 static to stagnation
Density ratio
0.2300
rho/rho0 static to stagnation
Pitot pressure ratio
5.6404
p02/p0 across a supersonic pitot shock
Specific heat ratio
gamma = 1.400
Air
Mach angle
30.00 deg
mu = sin^-1(1/M)
Prandtl-Meyer angle
26.38 deg
Isentropic turning limit
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