each other to form an apex the leading end of each prismatic vortex generators is inclined away from the direction of flow application_number US 60681109 A description fig1 shows a conventional engine inlet or duct 10 with an inner surface 14 over which air can flow a boundary layer 16 with a measurable thickness develops over the surface 14 as air flows over the surface 14 when air flows over the surface 14 at supersonic speeds shock waves 18 can be generated the shock waves 18 oscillate back and forth inside the engine inlet 10 and can cause the boundary layer 16 to separate from the surface 14 of the engine inlets 10 to attenuate this flow separation of the boundary layer a conventional rectangular vortex generator 20 can be located on the surface 14 the rectangular vortex generator 20 creates vortices than can help prevent flow separation as illustrated in fig2 a 2c a series of conventional rectangular vortex generators 20 can be located on the surface 14 and can be oriented at an angle relative to the direction of air flow although this conventional arrangement of rectangular vortex generators may attenuate flow separation at supersonic conditions the rectangular vortex generators 20 are not robust enough for the reliability maintainability and survivability desired as the rectangular faces 22 of the vortex generators 20 do not effectively tolerate the harsh pressure and aerodynamic loads heat erosion debris impact nor are these devices producible with standard manufacturing processes referring to fig3 a 3c an embodiment of a vortex generating system is shown comprising prismatic shaped vortex generators or structures 40 attached to the surface 14 of.