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:
Sep. 09, 2014

Filed:

Jun. 16, 2008
Applicant:

Detlev Schwetzler, Delmenhorst, DE;

Inventor:

Detlev Schwetzler, Delmenhorst, DE;

Assignee:

Airbus Operations GmbH, Hamburg, DE;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 23/06 (2006.01); B64C 7/02 (2006.01); B64D 29/02 (2006.01);
U.S. Cl.
CPC ...
B64C 7/02 (2013.01); B64D 29/02 (2013.01); B64C 23/06 (2013.01); Y02T 50/162 (2013.01);
Abstract

An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔.


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