Title:
SUPERSONIC EXTERNAL-COMPRESSION DIFFUSER AND METHOD FOR DESIGNING SAME
Document Type and Number:
WIPO Patent Application WO2001019675
Kind Code:
A3
Abstract:
A supersonic external-compression inlet (20) comprises a generally scoop-shaped supersonic compression section for diffusing a supersonic free stream flow (24). The supersonic compression section includes a main wall having a leading edge (28) and a throat portion downstream of the leading edge (28), and side portions joined to opposite side edges of the main wall so as to form a generally scoop-shaped structure. The side portions advantageously extend into the supersonic flow stream far enough to encompass the initial oblique shock wave that is attached to the leading edge of the main wall. The main wall has an inner surface (22) formed generally as an angular sector of a surface of revolution, the inner surface (22) of the main wall coacting with inner surfaces of the side portions to define a three-dimensional external-compression surface. The supersonic external-compression inlet (20) also includes a subsonic diffuser section arranged to receive flow from the supersonic compression section and to diffuse the flow to a subsonic condition. A variable-geometry inlet includes an external ramp hinged about its forward edge and forming a portion of the inner surface of the scoop-shaped diffuser, pivotal movement of the external ramp serving to vary a throat size of the inlet. The subsonic diffuser (20) includes an internal ramp hinged about its aft edge for maintaining a smooth transition from the external ramp.
Inventors:
HEDGES LINDA S
KONCSEK JOSEPH L
SANDERS BOBBY W
KONCSEK JOSEPH L
SANDERS BOBBY W
Application Number:
PCT/US2000/021796
Publication Date:
October 18, 2001
Filing Date:
August 09, 2000
Export Citation:
Assignee:
BOEING CO (US)
International Classes:
B64C30/00; B64D33/02; F02C7/042; F04D29/54; F04D29/56; (IPC1-7): B64D33/02; F02C7/04; F02C7/042
Foreign References:
| DE3447141A1 | 1986-07-03 |
Other References:
HUNTER L G, TRIPP J M, HOWLETT D G: "AIAA-85-1211 A Mach 2.0 Plus Supersonic Inlet Study Using the Navier-Stokes Equations", PROCEEDINGS OF THE AIAA/SAE/ASME/ASEE 21ST JOINT PROPULSION CONFERENCE, 6 November 1985 (1985-11-06), pages 1 - 11, XP000997783
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