Lifting-fuselage/wing aircraft having an elliptical forebody

Details Lifting-fuselage/wing aircraft having an elliptical forebody Lifting-fuselage/wing aircraft having an elliptical forebody

B - Operations, Transporting

64

C

B64C 1/00 (2006.01) B64C 21/00 (2006.01) B64C 23/00 (2006.01)

Patent

CA 2254880

An aircraft (6) having an elliptical fuselage (5) and low skin friction drag. The aircraft (6) includes (a) a lifting fuselage (5, 10) having a cross section constituting an airfoil in a majority of vertical planes taken parallel to the flight direction, and aspect ratio (ARf) of 0.33 to 1.10, a forebody having a substantially elliptic cross section (7) in all planes taken normal to the flight direction, and a substantially elliptic planform leading edge; (b) wings fixed to the fuselage (5, 10) having an aspect ratio (ARw) of at least 5.0; (c) a mechanism controlling aircraft attitude; and wherein the wings and fuselage (5) produce lift in varying proportions depending upon flight conditions as follows: (i) the aircraft (6) has a cruise design point in which the fuselage lift coefficient (CLF) is 0.08 or less, and (ii) the fuselage lift coefficient is at least 0.50 at an angle of attack (.alpha.LZo) of 10~, in level flight at sea level (ISA) with all movable left enhancing devices retracted.

Avion (6) à fuselage elliptique (5) et frottement superficiel réduit. L'avion (6) possède (a) un fuselage à effet porteur dont la section transversale forme un plan de sustentation dans la majorité des plans verticaux parallèles à la direction de vol, et présente un allongement compris entre 0,33 et 1,10 une partie avant avec une section transversale sensiblement elliptique (7) dan tous les plans perpendiculaires à la direction de vol, et un bord d'attaque planiforme sensiblement elliptique; (b) des ailes fixées au fuselage (5, 10) présentant un allongement d'au moins 5,0; (c) un mécanisme permettant de contrôler l'assiette de l'avion. Les ailes et le fuselage (5) produisent un effet de sustentation variant en fonction des conditions de vol, selon le modèle suivant: i) l'avion (6) se trouve à un point nominal de croisière dans lequel le coefficient de portance du fuselage est inférieur ou égal à 0,08, et ii) le coefficient de sustentation est d'au moins 0,50 pour un angle d'attaque (.alpha.LZo) de 10·, pour un vol en palier au niveau de la mer (ISA) avec tous les dispositifs mobiles externes en position rétractée.

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