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4. Consider a nozzle designed to deliver air from a large tank with stagnation pressure $P_0 = 200$ kPa and stagnation temperature $T_0 = 500$ K. At the nozzle exit the Mach number $Ma = 2.5$ and the mass flowrate is 3 kg/s. Assuming isentropic nozzle flow, calculate the following: (i) throat diameter. (ii) exit pressure. (iii) exit temperature. (iv) exit velocity. (v) exit diameter. The following equations can be used without proof: $\frac{T_0}{T} = 1 + \frac{k-1}{2}Ma^2$ $\frac{P_0}{P} = \left[1 + \frac{k-1}{2}Ma^2\right]^{\frac{k}{k-1}}$ $\dot{m}_{max} = \frac{0.6847P_0A^}{(RT_0)^{1/2}}$ $\frac{A}{A^} = \frac{1}{Ma}\left[\frac{2+(k-1)Ma^2}{k+1}\right]^{\frac{(k+1)/2(k-1)}{}}$

          4. Consider a nozzle designed to deliver air from a large tank with stagnation pressure $P_0 = 200$ kPa and stagnation temperature $T_0 = 500$ K. At the nozzle exit the Mach number $Ma = 2.5$ and the mass flowrate is 3 kg/s. Assuming isentropic nozzle flow, calculate the following:
(i) throat diameter.
(ii) exit pressure.
(iii) exit temperature.
(iv) exit velocity.
(v) exit diameter.
The following equations can be used without proof:
$\frac{T_0}{T} = 1 + \frac{k-1}{2}Ma^2$
$\frac{P_0}{P} = \left[1 + \frac{k-1}{2}Ma^2\right]^{\frac{k}{k-1}}$
$\dot{m}_{max} = \frac{0.6847P_0A^*}{(RT_0)^{1/2}}$
$\frac{A}{A^*} = \frac{1}{Ma}\left[\frac{2+(k-1)Ma^2}{k+1}\right]^{\frac{(k+1)/2(k-1)}{}}$

4 consider a nozzle designed to deliver air from a large tank with stagnation pressure p0 200 kpa and stagnation temperature t0 500 k at the nozzle exit the mach number ma 25 and the mass 40939

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