at the exit of the high speed inlet enters the ducted rotary flow controller and exits into the engine 0029 fig2 shows a partially exploded view of a high speed inlet 11 installed with a pulse detonation engine 12 with four combustion chambers 92 through 95 the chambers are open tubes that extend from the interface station 90 to the exit 91 the engine operates such that combustion indicated by the flashes 96 and 97 will occur in half of the chambers in this case 93 and 95 simultaneously for ease of understanding the rotary airflow controller 10 that would be installed at the interface station 90 between the inlet 11 and the engine 12 is shown at the side of the engine system the rotary airflow controller seals chambers 93 and 95 while firing occurs in them and allows airflow to fill chambers 92 and 94 rotation of the airflow controller 10 then opens chambers 93 and 95 for airflow while sealing 92 and 94 for combustion views of a rotary flow controller are shown in fig3 through 6 the rotary flow controller 10 illustrated in these figures represents a configuration that is designed to control the airflow into four combustion chambers of a pulse detonation engine the flow into the combustion chambers will normally consist of air it should be understood however that the term u201c airflow u201d as used herein is intended to encompass air gases and gaseous mixtures such as vaporized fuel the rotary flow controller 10 of fig3 through 6 is similar to a two bladed propeller the angular extent of the blades is selected during the aerodynamic design process.