Patent ID: 9482155
Filing Date: 2016-11-01
CPC Classification: B64C,B64D,F02C,F02K,F05D,Y10T

Claim Text:
1. An external compression inlet for use in a jet engine of the type including a compression surface having a foremost point and a cowl lip characterized by a cowl lip angle, the inlet comprising, in cross section: an initial segment disposed at a leading edge of said compression surface and inclined at a constant, initial turn angle α with respect to a free stream, said initial segment being configured to produce, at a predetermined design cruising speed, a bow shock which intersects an intersection point proximate said cowl lip; and a continuously curved segment aft of and structurally contiguous with said initial segment, said continuously curved segment being configured to cooperate with said initial segment to produce, at said predetermined design cruising speed, a terminal shock which extends from said intersection point to said compression surface; wherein, a local angle of inclination of each of a plurality of successive points along said continuously curved segment is relaxed relative to a traditional, unrelaxed isentropic surface, such that at said predetermined design cruising speed a plurality of said infinitesimally weak shocklets extend from a relaxed portion of said continuously curved segment and intersect said terminal shock aft of and spaced apart from said intersection point, and the plurality of said infinitesimally weak shocklets do not focus at said intersection point at said predetermined design cruising speed.