Relationship between vortex structure induced by secondary instability and experimentally observed vortex structure in a compressible shear layer were numerically investigated. Flow field experimentally investigated by Araki et al [1] was used. Subsonic air was in parallel injected into Mach 1.78 air stream. Sine or square-waved trailing edges were used for splitter plates. Phase of these plates consisting of injectors was in-phase (symmetric injector) or out-of-phase (asymmetric injector). Growth rate of shear layer and Pitotpressure distribution was compared with experimental results. There is a qualitative agreement between experimental and numerical results. From numerical results, some characteristic vortex structures found in previous studies on secondary instability of shear layer were found.
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