Experimental Study of Swept Impinging Oblique Shock/Boundary-Layer Interactions

An experimental investigation has been conducted on swept impinging oblique shock/boundary-layer interactions at a nominal Mach number of 2.28 with a fully turbulent incoming boundary layer (Reθ=5500). The swept impinging oblique shock is induced by shock generators with x-y plane deflection angle θ...

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Veröffentlicht in:	AIAA journal 2021-01, Vol.59 (1), p.140-149
Hauptverfasser:	Padmanabhan, Sathyan, Maldonado, Jorge C, Threadgill, James A. S, Little, Jesse C
Format:	Artikel
Sprache:	eng
Schlagworte:	Boundary layer interaction Engineering Engineering, Aerospace Flow visualization Fluid dynamics Mach number Ripples Science & Technology Separation Sweep angle Technology Topology Transducers Turbulent boundary layer
Online-Zugang:	Volltext
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