1. A certain nozzle expands a gas under isentropic conditions. nozzle entry velocity equals 90 m/sec, its final velocity 1500 the change in enthalpy of the gas? What percentage of error the initial velocity is neglected?
2. A rocket engine has following data: Propellant flow rate = 5.1 kg / s Nozzle exit diameter = 11 cm Nozzle exit pressure = 1.03 bar Ambient pressure = 1.013 bar Thrust chamber pressure = 20 bar Thrust = 6.8 kN. Find the follOWTing: Q) Exit Mach number (ii) Nozzle area ratio (iii)Throat area iv Pro weight flow coefficient (v) Characteristic velocity. Take specific heat ratio as 1.3.1
Its chamber or m/sec. What is is introduced if