A nozzle has an exit-to-throat area ratio

PHYSICS · Multi-part · Fermi University Physics · Fluids & Continuum Physics · Waves, acoustics and compressible flow · Waves, acoustics and compressible flow

Signal Speeds in Fluids, Ch Flow through nozzles: area change, choking and thrust

Problem

A nozzle has an exit-to-throat area ratio Ae/A∗=1.50A_{\rm e}/A^{*} = 1.50, fed by air (γ=1.4\gamma = 1.4) from a reservoir at stagnation pressure p0p_0. ((a)) Use the area-Mach relation to find the subsonic exit Mach number consistent with this area ratio, and the corresponding exit pressure as a fraction of p0p_0. ((b)) Find the supersonic exit Mach number consistent with the same area ratio, and its exit pressure as a fraction of p0p_0.

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