The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Nov. 01, 2016

Filed:

Sep. 27, 2012
Applicant:

Gulfstream Aerospace Corporation, Savannah, GA (US);

Inventors:

Timothy R. Conners, Savannah, GA (US);

Preston A. Henne, Savannah, GA (US);

Donald C. Howe, Savannah, GA (US);

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/04 (2006.01); B64D 33/02 (2006.01); B64C 30/00 (2006.01); F02K 7/10 (2006.01);
U.S. Cl.
CPC ...
F02C 7/04 (2013.01); B64D 33/02 (2013.01); B64C 30/00 (2013.01); B64D 2033/026 (2013.01); F02K 7/10 (2013.01); F05D 2220/80 (2013.01); F05D 2250/70 (2013.01); Y10T 29/49323 (2015.01); Y10T 137/0318 (2015.04); Y10T 137/0536 (2015.04);
Abstract

A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.


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