Document Type : Scientific extension

Authors

1 PhD Student Department of Mechanical Engineering, Tarbiat Modares University, Tehran, Iran

2 Associate Professor, Department of Mechanical Engineering, Tarbiat Modares University, Tehran, Iran

Abstract

Nowadays efforts for development of the scramjet engines are increased. Scramjet engines use atmospheric oxygen as an oxidizer therefore they don’t need oxidizer tanks, thus the weight of these systems is less than comparable rocket systems. Success of the air-breathing engines depends on the proper air-fuel mixing. In the case of hypersonic vehicles, air-fuel mixing issues increases. Sufficient mixing between the supersonic airstream and the fuel jet is critical for the design of scramjet engines. Air velocities in the scramjet combustors are in the order of the thousands meters per second and so the residence time for the fuel to mix with air is very short. In current study, two-dimensional flowfield of the jet injection into the supersonic flow investigate numerically using Fluent software. Two-dimensional Navier-Stokes equations and k-ω sst turbulence model and the perfect gas equation are solved numerically. The results of the numerical solution are compared and validated with experimental data.

Keywords

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