Supersonic aircraft jet engine installation
View Patent ↗Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following x o ) a region just ahead of the lip x l ) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.
1. A supersonic aircraft jet engine installation having engine inlet structure, comprising
a″) an inlet ramp and a cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip,
b″) the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following
x o ) a region just ahead of the lip
x l ) substantially to said lip,
c″) and wherein the ramp in an axial radial plane or planes has a first portion of relatively slight concavity configured to produce an initial shock system that extends from the said first portion generally forward of the said lip and within the flow path of air through the inlet structure, said ramp having a second and intermediate section that is relatively straight and located rearwardly of said ramp first portion, and configured to produce substantially constant Mach number flow, and followed in the flow direction by a third section of relatively shallow concavity configured to produce an additional and oblique shock system that extends from the said third section such that the additional shock system intercepts the said terminal shock at a position within the incoming air captured between the ramp system and said lip, said third section followed by an additional and fourth relatively straight section configured so as to produce a generally constant Mach number associated with the air proceeding through the middle portion of the inlet structure, and including a fifth section providing initial turning of the flow towards the engine ahead of the terminal shock, said fifth section extending uninterruptedly from said fourth section, said inlet system characterized as creating a compression and shock system and total pressure distribution that is intentionally non uniform across any axial plane located rearwardly of the terminal shock.
2. The structure of claim 1 on an aircraft engine having a nacelle, and including the aircraft fuselage and wing, the nacelle and cowl lapping the wing and located proximate the side of the fuselage.
3. The structure of claim 2 wherein the side of the fuselage facing the nacelle is indented.