The semi-freejet testing technique is used to demonstrate transition from rocket booster to ramjet sustainer at a specific flight condition with a maximum model size. For an existing ramjet model, three conditions limit optimal freejet nozzle sizing. First, the inlet model should be located in such a manner that the freejet nozzle will 'start' during the booster phase. Second, in the ramjet phase the oblique shock wave at the exit of the freejet nozzle will impinge on the inlet without disturbing the flow to the engine. Lastly, the maximum air flow rate that is available for the test is limited by the facility air reservoir. The design conditions and limits are summarized in a graph which defines the boundaries of the regime for sizing freejet nozzle and inlet axial location. A supersonic nozzle was constructed for a ramjet with an axisymmetric, external compression nose inlet. Successful transition tests were conducted in a low cost facility.
Sizing Supersonic Freejet Nozzle and Inlet Location for Simulation of the Transition Phase in Integral Rocket Ramjet
1990
4 pages
Report
No indication
English
Rocket Engines & Motors , Aerodynamics , Booster rocket engines , Free jets , Integral rocket ramjets , Ramjet engines , Supersonic inlets , Supersonic nozzles , Oblique shock waves , Engine design , Inlet flow , Nozzle design , Size (Dimensions) , Test facilities , Wind tunnel models , Foreign technology
Development of a Supersonic Inlet Capability for Integral Rocket Ramjet Applications
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