LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC AND SUPERSONIC CRUISE AIRCRAFT

Title:

LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC AND SUPERSONIC CRUISE AIRCRAFT

Document Type and Number:

WIPO Patent Application WO/2012/141770

Kind Code:

A3

Abstract:

Aircraft configured to operate at Mach numbers from above.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, and having one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.

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Inventors:

TRACY RICHARD R (US)
CHASE JAMES D (US)

Application Number:

PCT/US2012/020588

Publication Date:

December 06, 2012

Filing Date:

January 09, 2012

Export Citation:

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Assignee:

AERION CORP (US)

International Classes:

B64C3/10

Foreign References:

US7000870B2	2006-02-21
US7093792B2	2006-08-22
US6102328A	2000-08-15
US6834830B2	2004-12-28

Other References: