The detailed experimental investigations are implemented for better understanding of phenomena taking place under interaction of MW discharge in supersonic flow with aerodynamic bodies. The set of measures is undertaken for raising of precision and reliability of the obtained results: Modernization of the wind tunnel, improvement of existing and application of new diagnostic equipment. New digital Schlieren system is constructed. which allows obtaining single-shot images of bodies streamlining with time exposure about 0.5μs, synchronized with a certain phase of a process under investigation. The measuring channel, which registers the weak discharge afterglow, let us observe evolution of an excited gas region under its interaction with investigated body. Measurements of pressure on the body surface are also performed. Blunt cylinder, hemisphere and cone are tested as experimental bodies. Investigation of aerodynamic effect of plasma interaction with bodies over their dimension is fulfilled. The mutual position of MW discharge region and AD body is shown as having a substantial importance. Experimental evidence of vortex origination in a shock layer while its interaction with heated region of discharge is presented, this vortex being the basic reason for body drag reduction.
|Number of pages||9|
|State||Published - 1 Jul 2004|
|Event||42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States|
Duration: 5 Jan 2004 → 8 Jan 2004
|Conference||42nd AIAA Aerospace Sciences Meeting and Exhibit|
|Period||5/01/04 → 8/01/04|
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