Flow Prediction in Scramjet Engine Inlet

Abstract

The primary purpose of an inlet for any air-breathing propulsive system is to capture and compress air for processing by the remaining portions of the engine. In a conventional jet engine, the inlet works in combination with a mechanical compressor to provide the proper compression for the entire driving force. For vehicles flying at supersonic (1.5 < M < 5) or hypersonic (M > 5) speeds, suitable compression can be attained by the inlet without a mechanical compressor. Because the inlet channel provides the airflow and compression ratios of the scramjet engine, an efficiently designed inlet is critical for the successful operation of the engine. Scramjet inlets are a key component in its function, and their design has stantial in several aspects. A computational study for scramjet inlet with different ramp angles and ramp lengths are analyzed to compress the air by sharp leading edge, fixing the whole cowl up or down. However, the performance of the inlet tends to degrade as Mach number range increases an air intake consisting of different ramps producing oblique shocks followed by a cowl shock. An imposing shock may force the boundary layer to separate from the wall,resulting in total pressure regaining losses and a reduction of the inlet efiiciency. Design an inlety to meet the necessities such as Low stagnation pressure loss, High static pressure and temperature increases and deceleration of flow to the desired value of mach number. A two-dimensional analysis was carried out in this project. ANSYS is used to create the Geometry. ICEM is used to create the mesh & FLUENT is used for analyzing the flow.