Abstract
An experimental investigation of a simple. two-dimensional resonance tube has been conducted. The leading edge of the resonance tube was biunt in order to simulate the geometric configuration of proposed rocket ignition systems. Thermodynamic characteristics of the fluid near the endwall were determined for a range of jet stagnation pressures, nozzle-resonance tube separation distances, and resonance tube lengths. Strong resonance, as indlceted by high endwall temperatures, was obtained for both supercritical and subcritical jet pressure ratlos. The latter results are of particular signlficance for the design of resonance tube ignitlon systems. ._
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