Abstract:
The main thesis of this paper is to analyze the effect of inlet center body (spike) extending forwardly of the cowl inlet capture area of adjustable air inlet of variable geometry, for a supersonic aircraft, to continuously and effectively regulate the incoming air throughout the aircraft operating range of idle, subsonic, sonic and supersonic speeds. This is done by axially translating the inlet center body, for positioning of an external or initial shock wave front such that it extends conically between the apex of the spike and leading edge of the cowl for external
supersonic spillage of the air thereby regulating the engine air mass requirements. The main object is to provide inlet which is adjustable to match engine air flow characteristics while achieving high performance through high pressure recovery and low drag. In this a movable spike is utilized at supersonic speed for regulating both external supersonic low drag spillage and internal throat supersonic diffusion and the results are analyzed using CFX solver computationally.
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