Step 1: Choked condition.
At throat: $M=1$ (fixed).
Step 2: Temperature.
\[ T_t = f(T_0) \Rightarrow \text{constant since } T_0 \text{ constant.} \]
Step 3: Velocity.
\[ u = M a = a = \sqrt{\gamma RT_t} \Rightarrow \text{constant.} \]
Step 4: Pressure & density.
Ratios $p_t/p_0$ and $\rho_t/\rho_0$ are fixed. Increasing $p_0$ raises both $p_t, \rho_t$. \[ \boxed{u, M, T \text{ constant; } p, \rho \text{ increase.}} \]
An aircraft is flying at an altitude of 4500 m above sea level, where the ambient pressure, temperature, and density are 57 kPa, 259 K, and 0.777 kg/m\(^3\), respectively. The speed of the aircraft \( V \) is 230 m/s. Gas constant \( R = 287 \, {J/kg/K} \), and specific heat ratio \( \gamma = 1.4 \). If the stagnation pressure is \( p_0 \), and static pressure is \( p \), the value of \[ \frac{p_0 - p}{\frac{1}{2} \rho V^2} \] is __________ (rounded off to two decimal places).