76 is varied and controlled by a fifth linear actuating means e which is operably disposed between a first lever 78 cantilevered off the forward section 42f and a second lever 80 cantilevered off the aft section 42a the first and second levers when actuated by the fifth linear actuating means e rotates aft section 42a about the aft end of the forward section 42f about the aft wall hinge 74 hinge so as to vary the intermediate ramp angle 76 the breadth of the present invention as claimed herein encompasses the use of one or more intermediate ramp angles on the forwardmost wedge wall as well as those aft and on both fixed and variable forwardmost wedge angles at the leading edge of the wedge operation of the variable wedge and ramp angles may be combined with the upper rotatable cowl leading edge ramp 26 and the lower rotatable cowl leading edge ramp 27 in fig1 resulting in an inlet geometry which produces a balanced shockwave system at all supersonic flight mach numbers and for which the cowl shockwave always impinges between the forebody 19 and the afterbody 19a of the telescoping center wedge 12 at the throat 35 of the diffuser 4 an important advantage of the impinging cowl shockwave always intersecting the center wedge throat is simplification and increased efficiency of the center wedge boundary layer bleed system this eliminates the need to proportionally enlarge the region of surface boundary layer bleed.