Oblique blended wing body aircraft

An oblique wing aircraft designed for reduced surface area to volume ratio, said aircraft having an oblique wing comprising:

• a forward-swept wing segment on one side of the wing and an aft-swept wing segment on the opposite side of the wing, wherein a straight line projection of a predominant leading edge of one of said forward-swept and said aft-swept wing segments passes behind a straight line projection of a predominant trailing edge of the other wing segment at a vehicle centerline;
• a center oblique wing section connecting said forward-swept wing segment and said aft-swept wing segment, said center oblique wing section having a larger chord length near its centerline than the maximum chord length of either said forward-swept wing segment or said aft-swept wing segment;
• the forward and aft end of said center oblique wing section having a forward-swept transition area and aft-swept transition area where the chord length of said transition areas taper down more rapidly than said forward-swept or aft-swept wing segments as said center oblique wing section extends outboard toward said forward-swept wing segment and aft-swept wing segment;
• said aircraft having the majority of its volume in said center oblique wing section;
• said aircraft being capable of minimizing drag by flying at higher yaw angles when flying at transonic speed.

An asymmetric aircraft, said aircraft comprising a center wing section and left and right outboard primary wing segments,

• said center wing section connecting said left and right outboard primary wing segments, said center wing section having a larger chord length near its centerline than the chord length of either of said left or right outboard primary wing segments;
• the ends of said center wing section having a left and right transition area where the chord length of said transition areas taper down more rapidly than said left or right outboard primary wing segments as said center wing section extends outboard toward said left and right outboard primary wing segments;
• said aircraft having the majority of its volume in said center wing section;
• said aircraft having a plan view layout wherein one side of the outline of the primary aerodynamic structure of the aircraft differs substantially from a mirror image of the other side of the outline of the primary aerodynamic structure of the aircraft;
• said aircraft being substantially free of horizontal tail surfaces;
• and wherein a straight line projection of a predominant leading edge of one of said left and right outboard primary wing segments passes behind a straight line projection of a predominant trailing edge of the other outboard primary wing segment at a vehicle centerline.