Patent ID: 8672259

Claim:
A supersonic aircraft including a body, two wings and two engine nacelles; each said nacelle extending below a said wing and located at part-span; said body including a fuselage and a keel; said keel disposed lengthwise below said fuselage; a main landing gear including two struts and two wheel bogies; each said strut pivoted at one end in a said wing substantially inboard of a said nacelle; each said strut carrying at its other end a said wheel bogie; after takeoff, each said strut pivoting upward, lifting a said wheel bogie toward said keel; said keel having doors for entry of said wheel bogies, and having some volume for storing said wheel bogies; one said strut's pivoting including a forward component; the other said strut's pivoting including a backward component; said wheel bogies thereby stored one behind the other, partly or wholly in said keel; such tandem storage allowing said keel to be much narrcwer than said fuselage; the exterior surface under said fuselage comprising two bottom strips not including said keel; each said bottom strip constituting a lengthwise area spanning the narrow width between said keel and the root portion of a said wing; said wings positioned low, each one adjoining said fuselage at or near a said bottom strip; each said wing having a lower surface inboard of a said nacelle but outboard of a said bottom strip; a said lower surface together with a said bottom strip making a large expanse substantially spanning the area between a said nacelle and said keel; a said nacelle having two air inlet openings at the front; said openings side-by-side and separated by a substantially vertical nose wedge; said nose wedge located ahead of several ramps each being part of the airflow ducts ultimately conveying intake air to several engines in said nacelle's rear; a said nacelle's front half having tapered sides angling narrower toward said openings; when supersonic, said nose wedge or said tapered sides, or both, creating at least two oblique shocks trailing backward at some angle from opposite said sides of a said nacelle; first said oblique shock crossing under said large expanse; the air pressure rise behind said first oblique shock pushing up on some of said large expanse, thereby generating compression lift; said keel extending farther back along said aircraft than said nose wedge; and said keel intercepting said first oblique shock, causing a reflected shock effect and increasing said compression lift.