Shockless supersonic aircraft

Claim 1

AN AIRCRAFT TO OPERATE AT SUPERSONIC SPEEDS, SAID AIRCRAFT COMPRISING A WING AND A FUSELAGE, SAID FUSELAGE HAVING A NOSE AND TAIL AND AN EXTERIOR SUBSTANTIALLY PARALLEL TO THE FREE STREAM OF AIR FLOW BEGINNING AT SAID NOSE AND MAINTAINING A SUBSTANTIALLY UNIFORM CROSS SECTION AND BEING FURTHER PROVIDED WITH A FAIRED CLOSURE AT ITS TAIL, SAID FUSELAGE HAVING AN APERTURE AT ITS NOSE BOUNDED BY SAID EXTERIOR SURFACES, SAID WING HAVING LEADING AND TRAILING EDGES AND HAVING UPPER AND LOWER SURFACES, SAID WING HAVING AN APERTURE ALONG ITS LEADING EDGE BOUNDED BY SAID UPPER AND LOWER SURFACES, SAID UPPER WING SURFACE BEING CONVEX AS TO PROVIDE UPPER SURFACE SUCTION LIFT, SAID LOWER SURFACE BEING SUBSTANTIALLY PARALLEL TO THE FREE STEAM AIR FLOW ADJACENT SAID LEADING EDGE, THERE BEING A JET OPENING AT SAID LOWER SURFACE UPSTREAM FROM SAID TRAILING EDGE, SAID LOWER SURFACE BEING CONCAVE DOWNSTREAM FROM SAID OPENING TO THE TRAILING EDGE CLOSURE, SAID FUSELAGE AND SAID WING RESPECTIVELY HAVING DUCT MEANS OF CONTRACTING CROSS SECTIONS, THERE BEING ENERGIZING MEANS IN SAID FUSELAGE AND WINGS TO PULL IN THE AIR ENTERING SAID APERTURES AND TO MAINTAIN AN IRROTATIONAL VELOCITY PROFILE IN SAID DUCT MEANS TO MINIMIZE SHOCK DISSIPATION, THERE BEING ADDITIONAL MEANS TO EXHAUST SAID AIR AFTER BEING ENERGIZED BY SAID ENERGIZING MEANS ALONG SAID CONCAVE SURFACE OF SAID WING TO PROVIDE LOWER SURFACE PRESSURE LIFT.