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Isentropic Flow

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Calculate thermodynamic properties across an isentropic flow. Isentropic flow is a flow process where entropy remains constant, which occurs in ideal compressible flow with no heat transfer or friction.

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
ρ/ρ₀ static to stagnation
Pitot pressure ratio
5.6404
p₀₂/p₀ across a supersonic pitot shock

Specific heat ratio

γ = 1.400

Air

Mach angle

30.00°

μ = sin⁻¹(1/M)

Prandtl-Meyer ν

26.38°

isentropic turning limit

Flow map

Nozzle area trades static pressure for velocity

Throat A*Reservoir / Low MachExpanded StreamM 2.000μ 30.0°

Static ratios versus Mach number

Mach = 2.000

p/p₀
T/T₀
ρ/ρ₀

Current Mach

2.000

p/p₀

0.12780

T/T₀

0.55556

ρ/ρ₀

0.23005

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