Across an oblique shock wave formed over a compression corner in steady supersonic flow, which of the following thermodynamic flow properties remains constant?

(A) Total temperature (T_0)

(B) Total pressure (p_0)

(C) Static density (\rho)

(D) Normal component of Mach number (M_n)

Answer Key:

A

### 5-Stage Derivation & Analytical Solution: 1. **Stage 1: Governing Energy Equation:** $h_1 + \frac{V_1^2}{2} = h_2 + \frac{V_2^2}{2} = h_0$. 2. **Stage 2: Calorically Perfect Gas:** $h_0 = c_p T_0 = \text{constant} \implies T_{01} = T_{02}$. 3. **Stage 3: Other Properties:** Total pressure $p_0$ drops, static density $\rho$ increases, normal Mach $M_n$ drops below 1. 4. **Stage 4: Selection:** Option A is correct.

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