Nozzle Analysis: Variations in Mach Number and Pressure Along a Converging and a Converging-diverging Nozzle

Consider the flow through a rocket engine nozzle. Assume that t... | Filo

An ideal gas with k=1.4 is flowing through a nozzle such that the Mach number is 1.6 where the flow area is 45  cm^2. Approximating the flow as isentropic, determine the flow area at the location where the Mach number is 0.8 . | Numerade

Flow Nozzle Principle, Advantages, Disadvantages & Applications

6. Consider the flow through a rocket engine nozzle. Assume thatthe gas flow through the nozzle is an isentropic expansion of acalorically perfect gas. In the combustion chamber, the gas whichresults from the combustion of rocket fuel and oxidizer is at apressure of 15 atm and a temperature of 2500 K. The molecularweight and specific heat at constant pressure are 12 and 4157J/(kgK) respectively. The gas expands to supersonic speed through thenozzle, with a temperature of 1350 K at the nozzle exi

Consider the isentropic flow through a supersonic nozzle. If th... | Filo

consider the isentropic supersonic flow through a convergent divergent nozzle with an exit to throat area ratio of 1025 the reservoir pressure and temperature are 5 atm and 600r respectively 39793

SOLVED:A normal shock occurs in the diverging section of a converging-diverging nozzle where A=25 cm^2 and M= 2.75 . Upstream, T0=550 K and p0=700 kPa(abs) . The nozzle exit area is 40 cm^2. Assume the flow is isentropic except across the shock. Determine the nozzle exit pressure, throat area, and mass flow rate.

Steam enters a converging nozzle at 800 kPa and 553.15 K(280^∘ C) with negligible velocity. If expansion is isentropic, what is the minimum pressure that can be reached in such a nozzle and what is the cross-sectional area at the nozzle throat at this pressure for a flow rate of 0.75 kg s^-1 ? | Numerade