Described are a number of aerodynamic investigations performed to assess the possibilities to introduce a ramjet engine in a missile body of conventional lay-out. A schematic of a existing rocket propelled missile was selected as a reference configuration and a number of cruciform aft inlet systems were investigated. The Mach number range studied was 1.6 to 2.4 with bulk of the data taken around M = 2. The investigations cover the following areas: (1) measurement of missile drag properties; (2) check of missile aerodynamic performance; (3) selection of inlet type; (4) performance calibration of aft inlets; (5) effect of missile forebody geometry on inlet performance; and (6) development of engine control system reference pressure probes. It was concluded that introduction of the selected aft inlet system causes only small changes in missile drag and other aerodynamic properties. Used with a constant geometry ramjet engine the inlet and reference pressure probe combination provides 70% excess thrust at zero angle of attack and allows sustained flight at 5 to 6 deg angle of attack with the selected missile configuration. (Author)
Development of Aft Inlets for a Ramjet Powered Missile
1972
47 pages
Report
No indication
English
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