Numerical investigation of back pressure and free-stream effects on a mixed compression inlet performance

作者：Ebrahimi A^*; Chavoshi M Zare

来源：Scientia Iranica, 2018, 25(2): 751-761.

DOI：10.24200/sci.2017.4324

• Mixed compression inlet
• Performance parameters
• Multi-block grid
• Spalart-Allmaras turbulence model
• Roe's approximated Riemann solver

Inlet performance has an important role in the operation of air-breathing propulsion systems. In this study, performance of a supersonic axisymmetric mixed-ion inlet i the supercritical operating condition is numerically studied. The effects of free-stream Mach number and engine-face pressure on performance parameters, including mass flow ratio, drag coefficient,, total ressure recovery, and flow distortion, are investigated. For this sake, a multi-block density-based finite volume CFD code is developed, and Reynolds-averaged Navier-Stokes equations with Spalart,-Alima,as lnequation- turbulece model are employed. 'The cod is validated by comparing numerical results against, other computational results and experimental data for two test, cases of inviscid flow in a two-dimensional mixed-compression inlet and flow in an external compression inlet. Finally, the code is utilized for the investigation of a specific supersonic mixed-compression inlet with the design Mach number of 2.0 and length-1,0-diamtor ratio of 3.1. Results revealed that, the increment, of free-stream Mach number leads to the decrease in total pressure recovery and drag coefficient, while mass flow ratio and flow distortion increase. The effects of engine-face pressure on performance parameters showed that by increasing the engine-face pressure, mass flow ratio and drag coefficient remain constant, while total pressure recovery increases and flow distortion decreases.

• 出版日期2018-4