SYSTEMS AND METHODS FOR CONFIGURING AIRCRAFT TO MEET PERFORMANCE GOALS AND SHOCK WAVE DISTURBANCE CONSTRAINTS

Title:

SYSTEMS AND METHODS FOR CONFIGURING AIRCRAFT TO MEET PERFORMANCE GOALS AND SHOCK WAVE DISTURBANCE CONSTRAINTS

Document Type and Number:

WIPO Patent Application WO2005047102

Kind Code:

A3

Abstract:

An aircraft (400) for low sonic boom supersonic flight conditions includes a wing (404) with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled to account for the equivalent area reduction due to excursions below to goal curve. A relaxed constraint allows the equivalent area distribution of the aircraft (400) to be at or below the equivalent area distribution goal curve to enable multiple parameters to be configured to meet the equivalent area distribution constraint, as well as other constraints. The shape of a reflexed portion (424) of the airfoil (302) on the underside of the wing (314), and a corresponding shape for the upper surface of the nacelle (306) provide favorable interaction between the wing (314) and the nacelle (306).

Inventors:

MORGENSTERN JOHN (US)
ARSLAN ALAN (US)
BARBIERI JOSHUA (US)
BACH JAMES (US)

Application Number:

PCT/US2004/036892

Publication Date:

December 22, 2005

Filing Date:

November 04, 2004

Export Citation:

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Assignee:

MORGENSTERN JOHN (US)
ARSLAN ALAN (US)
BARBIERI JOSHUA (US)
BACH JAMES (US)
SUPERSONIC AEROSPACE INTERNAT (US)

International Classes:

B64C1/00; B64C30/00; B64D27/18; (IPC1-7): B64C30/00

Foreign References:

US2997256A	1961-08-22
US3310262A	1967-03-21
US4598886A	1986-07-08
US6588703B1	2003-07-08

Other References:

DARDEN C.M.: "Sinic Boom Minimization With Nose Bluntness Relaxation", NASA TECHNICAL PAPER 1348, 1979, pages 1 - 51, XP002369344

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