Numerical study of a supersonic open cavity flow and pressure oscillation control

Numerical experiments examined the flow structure and suppression of pressure oscillation in the M equals 2.5 supersonic open cavity flow problem. The results show that the large pressure variation within the cavity induced by the shear layer's wavy shape produces new vortices not found in situ...

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Veröffentlicht in:	Journal of aircraft 1995-03, Vol.32 (2), p.363-369
Hauptverfasser:	Jeng, Yih Nen, Payne, Uon Jan
Format:	Artikel
Sprache:	eng
Schlagworte:	Aerodynamics Aviation Compressible flows shock and detonation phenomena Exact sciences and technology Flow control Fluid dynamics Fundamental areas of phenomenology (including applications) Physics Supersonic and hypersonic flows
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Beschreibung
Zusammenfassung:	Numerical experiments examined the flow structure and suppression of pressure oscillation in the M equals 2.5 supersonic open cavity flow problem. The results show that the large pressure variation within the cavity induced by the shear layer's wavy shape produces new vortices not found in situations where M is less than 2.5.
ISSN:	0021-8669 1533-3868
DOI:	10.2514/3.46724