Patent ID: 7568347
Filing Date: 2009-08-04
Classification: G06F,Y02T,Y10T

Abstract:
1. A method of designing a hypersonic inlet for an aircraft, the method comprising: (a) establishing a centerline geometry for a flowfield generator (FFG); (b) establishing spanwise contours for the FFG; (c) gridding and running computational fluid dynamics (CFD) for the FFG; (d) iterating steps (a) through (c) until a desired inlet aperture flow characteristics uniformity, and geometrical constraints are achieved; (e) streamline tracing a diverterless hypersonic inlet (DHI) forebody within a three-dimensional, FFG CFD solution and transferring the streamlines into a computer aided design (CAD) environment; and (f) surfacing streamlines of the DHI forebody in the CAD environment and consolidating them with an inlet aperture design.