If the rocket exhaust gases are calorically perfect and have a mean molecular mass of 28 kg/kmol, and a constant specific heat ratio (γ) of 1.33, determine the nozzle exit velocity. Assume the nozzle inlet conditions to be the following: P1 = 5 MPa, V1 = 240 m/s, T1 = 750 K and exit pressure (Pe) to be 1 MPa.

• A. 204 m/s
• B. 699.21 m/s
• C. 712.32 m/s
• D. 805.56 m/s
• E. to be 1 MPa.a) 204 m/sb) 699.21 m/sc) 712.32 m/sd) 805.56 m/s