Aerodynamic Design and Analysis of Intake for Hypersonic Air-breathing Vehicle using CFD Approach

摘要

A mixed compression air-intake has initially been designed using two-dimensional oblique shock method and subsequently refined by analysis using computational fluid dynamic software PARAS 3D. The design is aimed to get the required intake exit condition, which is compatible with scramjet combustor of a hypersonic flying vehicle at Mach 6.5. Effects offorebody side fence on the intake characteristics ha ve been analyzed. The pressure distribution on body and cowl evaluated using 2D oblique shock method is compared with the computed results. Intake geometry has been appropriately modified based on the NS computations. Intake performance parameters, such as, total pressure recovery, mass flow captures, axial force coefficient and entry and exit conditions a t design and off-design angle of attack conditions ha ve also been analyzed on the selected configuration. Effect of sideslip angle on the intake performance is found quite significant both at design and off-design angle of attack conditions.