Determine the static pressure rise across the diffuser

Reference no: EM131036244

An aircraft flies with a Mach number Ma1 =0.8 at an altitude of 7000 m where the pressure is 41.1 kPa and the temperature is 242.7 K. The diffuser at the engine inlet has an exit Mach number of Ma2 =0.3. For a mass flow rate of 65 kg/s, determine the static pressure rise across the diffuser and the exit area.

Reference no: EM131036244

Questions Cloud

Treat the steam as an ideal gas with k =1.3 : plot the exit pressure, the exit velocity, and the mass flow rate through the nozzle versus the back pressure Pb for 6.0 ≥ Pb c ≥ 3.0MPa. Treat the steam as an ideal gas with k =1.3, cp= 1.872 kJ/kg · K, and R =0.462 kJ/kg · K.

Find the expression for the ratio of the stagnation pressure : Find the expression for the ratio of the stagnation pressure after a shock wave to the static pressure before the shock wave as a function of k and the Mach number upstream of the shock wave Ma1.

Dysfunctional performance measurement in theory : Critically analyse the institutional, organisational and individual influences on management accounting systems and Form professional judgments about the appropriateness of the design and operation of management accounting systems

Fourth year with statewide services corporation : Mary Corey recently completed her fourth year with statewide Services Corporation. In her position as costumer support specialist, she consistently received high performance evaluations-until recently. Indeed, her most recent evaluation, completed..

Determine the static pressure rise across the diffuser : The diffuser at the engine inlet has an exit Mach number of Ma2 =0.3. For a mass flow rate of 65 kg/s, determine the static pressure rise across the diffuser and the exit area.

Calculate the throat and exit areas for a mass flow rate : Calculate the throat and exit areas for a mass flow rate of 0.25 kg/s, assuming the nozzle is isentropic. Why must this nozzle be converging- diverging?

Why must this nozzle be converging- diverging : Helium expands in a nozzle from 150 psia, 900 R, and negligible velocity to 15 psia. Calculate the throat and exit areas for a mass flow rate of 0.2lbm/s, assuming the nozzle is isentropic.

Problem regarding isolation or incremental basis : a) Calculate the relevant cash flows either on an isolation or incremental basis. b) Calculate the NPV and IRR of the project and advise whether the company should replace the manual machine.

Provide a brief analysis of the client solvency : MAA705 - Corporate Auditing - Individual Assignment. Solvency- Provide a brief analysis of the client's solvency. Based on your findings, name three accounts which should be investigated throughout the audit and provide justification for your choic..

User Account

All Pages