Patent ID: 6098922
Filing Date: 2000-08-08
Classification: B64C,Y02T

Abstract:
An aircraft comprising:(a) a lifting fuselage having a cross-section constituting an airfoil in a majority of vertical planes taken parallel to the flight direction and an aspect ratio (AR.sub.f) of 0.33 to 1.10;(b) wings fixed to the fuselage having an aspect ratio (AR.sub.w) of at least 5.0;(c) a mechanism controlling aircraft attitude; and(d) a mechanism propelling the aircraft;wherein the wings and fuselage produce lift in varying proportions depending upon flight conditions as follows:(i) the aircraft has a cruise design point in which the fuselage lift coefficient (C.sub.LF) is 0.08 or less, and(ii) the fuselage lift coefficient is at least 0.50 at an angle of attack (.alpha..sub.LZo) of 10.degree., in level flight at sea level (ISA) with all movable lift enhancing devices retracted; andwherein the aircraft has a maximum L/D value of 16 or more.