Engine pod for an aircraft with a vortex generator arrangement
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United States of America Patent
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May 22, 2012
Grant Date -
Nov 26, 2009
app pub date -
May 26, 2009
filing date -
May 26, 2008
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Abstract
An engine pod for an aircraft has one side which features several fin-shaped vortex generators such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases. The first vortex generator lies within a positioning corridor that is situated between two boundary lines. The origin and end points, respectively, of the first boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and 25 degrees and the longitudinal engine pod coordinate X=L/4 and L·⅔. The origin and end points, respectively, of the second boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and 55 degrees and the longitudinal engine pod coordinate X=L/4 and L·⅔.
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