INLET DIFFUSER FOR JET ENGINE AND METHOD FOR DIFFUSING INCOMING AIR OF JET ENGINE
FIG8 is a flowchart depicting methods of diffusing incoming air according to the present disclosure 
FIG8 schematically provides a flowchart that represents illustrative, non-exclusive examples of methods according to the present disclosure. In FIG8, some steps are illustrated in dashed boxes indicating that such steps may be optional or may correspond to an optional version of a method according to the present disclosure. That said, not all methods according to the present disclosure are required to include the steps illustrated in solid boxes. Additionally, the order of steps illustrated in FIG8 is exemplary, and in different embodiments the steps in FIG8 may be performed in a different order. The methods and steps illustrated in FIG8 are not limiting and other methods and steps are within the scope of the present disclosure, including methods having greater than or fewer than the number of steps illustrated, as understood from the discussions herein. FIG8 is a flowchart depicting methods 800, according to the present disclosure, of mixing boundary layer air in an inlet diffuser of a jet engine. Methods 800 include receiving air into an internal volume (e.g., internal volume 16) defined by a body (e.g., diffuser body 14) of the inlet diffuser at 802. For example, the air may correspond to ambient air outside of the inlet diffuser that flows into the internal volume via an inlet aperture (e.g., inlet aperture 12). According to the present disclosure, the inlet aperture may have a high aspect ratio.
flowchart
812
inboard direction at
810
at
804
splitting at
816
jet engine at
802
inlet diffuser at
814
at
800
Methods
808
boundary layer air in
806
at
['2. The inlet diffuser (10) of claim 1, wherein said inlet (12) is defined as having a maximum width (40) and a maximum height (50), wherein the maximum width (40) is at least 2, at least 3, at least 4, or at least 5 times the maximum height (50).', '9. The inlet diffuser (10) of claim 1, wherein a perpendicular distance (62) between the internal surface (20) and the apex portion (64) of the wall face (310) at a particular location of the wall face (310) is greater than an expected thickness (56) of the first portion (36) of boundary layer air in a channel region (70) proximate to the particular location of the wall face (310) when the first portion (36) of boundary layer air flows within the channel (70) at normal operating velocities.']