In gas dynamics, the Kantrowitz limit refers to a theoretical concept describing choked flow at supersonic or near-supersonic velocities. When an initially subsonic fluid flow experiences a reduction in cross-section area, the flow speeds up in order to maintain the same mass-flow rate, per the continuity equation. If a near supersonic flow experiences an area contraction, the velocity of the flow will decrease until it reaches the local speed of sound, and the flow will be choked. This is the principle behind the Kantrowitz limit: it is the maximum amount of contraction a flow can experience before the flow chokes, and the flow speed can no longer be increased above this limit, independent of changes in upstream or downstream pressure.
Derivation of Kantrowitz limit Assume a fluid enters an internally contracting nozzle at cross-section 0, and passes through a throat of smaller area at cross-section 4. A normal shock is assumed to start at the beginning of the nozzle contraction, and this point in the nozzle is referred to as cross-section 2. Due to conservation of mass within the nozzle, the mass flow rate at each cross section must be equal:
m ˙ 0 = m ˙ 2 = m ˙ 4 {\displaystyle {\dot {m}}_{0}={\dot {m}}_{2}={\dot {m}}_{4}}
For an ideal compressible gas, the mass flow rate at each cross-section can be written as,
m ˙ 0 = γ R M 0 ( 1 + γ − 1 2 M 0 2 ) − γ + 1 2 ( γ − 1 ) p t 0 A 0 T t 0 {\displaystyle {\dot {m}}_{0}={\sqrt {\frac {\gamma }{R}}}M_{0}\left(1+{\frac {\gamma -1}{2}}M_{0}^{2}\right)^{-{\frac {\gamma +1}{2(\gamma -1)}}}{\frac {p_{t0}A_{0}}{\sqrt {T_{t0}}}}}
m ˙ 4 = γ R M 4 ( 1 + γ − 1 2 M 4 2 ) − γ + 1 2 ( γ − 1 ) p t 4 A 4 T t 4 {\displaystyle {\dot {m}}_{4}={\sqrt {\frac {\gamma }{R}}}M_{4}\left(1+{\frac {\gamma -1}{2}}M_{4}^{2}\right)^{-{\frac {\gamma +1}{2(\gamma -1)}}}{\frac {p_{t4}A_{4}}{\sqrt {T_{t4}}}}}
where A {\textstyle A} is the cross-section area at the specified point, γ {\textstyle \gamma } is the Isentropic expansion factor of the gas, M {\textstyle M} is the Mach number of the flow at the specified cross-section, R {\textstyle R} is the ideal gas constant, p t {\textstyle p_{t}} is the stagnation pressure, and T t {\textstyle T_{t}} is the stagnation temperature. Setting the mass flow rates equal at the inlet and throat, and recognizing that the total temperature, ratio of specific heats, and gas constant are constant, the conservation of mass simplifies to,
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