 Solution

ID: past-exam-of-the-mathematics-course-of-the-university-of-cambridge/2026/ii/paper-4/39c/b/solution

Codex  0 Created 2026-09-24 Updated 2026-09-25

c^{2} = γ p / ρ

eliminate the density and pressure ratios. The result is

M_{2}^{2} = \frac{2 + ( γ - 1 ) M _{1}^{2}}{2 γ M _{1}^{2} - ( γ - 1 )},

so a supersonic upstream flow becomes subsonic.

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