US 12,391,357 B2
Aircraft design and technology
Luc Van Bavel, Quebec (CA); Michael Derman, Bend, OR (US); Jeffrey A. Gamon, Wichita, KS (US); Ian Gilchrist, Bellevue, WA (US); James Donn Hethcock, Jr., Colleyville, TX (US); Dieter Koehler, Powell Butte, OR (US); David W. Levy, Parker, CO (US); Michael Matarrese, Boulder, CO (US); Luke A. Thompson, Centennial, CO (US); and Robert David Wyatt, Fort Worth, TX (US)
Assigned to FREEDOM AIRCRAFT VENTURES LLC, Sparks, NV (US)
Filed by Freedom Aircraft Ventures LLC, Sparks, NV (US)
Filed on Apr. 19, 2021, as Appl. No. 17/301,893.
Application 17/301,893 is a division of application No. 16/223,011, filed on Dec. 17, 2018.
Claims priority of provisional application 62/607,285, filed on Dec. 18, 2017.
Prior Publication US 2021/0354804 A1, Nov. 18, 2021
Int. Cl. B64C 1/00 (2006.01); B64C 1/26 (2006.01); B64C 3/10 (2006.01); B64C 5/02 (2006.01); B64C 9/22 (2006.01); B64D 27/14 (2006.01); B64C 39/00 (2023.01)
CPC B64C 1/0009 (2013.01) [B64C 1/26 (2013.01); B64C 3/10 (2013.01); B64C 5/02 (2013.01); B64C 9/22 (2013.01); B64D 27/14 (2013.01); B64C 39/00 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An aircraft, comprising:
a fuselage;
a swept wing extending laterally relative to the fuselage at an angle less than 45° relative to a line that is normal to a length dimension of the fuselage, the wing having an aspect ratio of at least 4;
at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the wing;
at least one vertical tail surface extending upward from the fuselage;
at least one engine mounted to the fuselage at a location positioned vertically below the wing, the at least one engine operable to generate thrust;
leading edge root extensions mounted to the wing and the fuselage at a leading edge of the wing, wherein a span of the leading edge root extensions is from about one quarter to about three quarters of a width of an inlet duct of the at least one engine in size;
a dynamic slat attached to a leading edge of the wing, wherein the aircraft has a thrust to weight ratio in the range of about 0.5 to about 0.6, wherein the aircraft makes sustained turns in the range of about 6.5 G to about 7.5 G and the aircraft makes sustained turns at an angle of attack of at least 25°, wherein the leading edge root extensions having a planform area ratio relative to a planform area of the wing in the range of about 0.1% to about 5%.