Effect of slot width on transition and noise attenuation of a sound shield panel for supersonic wind tunnelsThe effect of slot width on transition and noise attenuation of a planar rod wall sound shield has been investigated at Mach 6. Boundary layer laminarization was obtained by induced suction through adjustable slots or gaps between the rods. Transition Reynolds numbers increased significantly with increasing gap width. The local mean flow field above the suction panel rod array was uniform. Important factors for design and performance of a supersonic wind-tunnel sound shield are rod diameter, gap-to-rod diameter ratio, surface finish of the rods, and leading-edge configuration.
Document ID
19760055681
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Harvey, W. D. (NASA Langley Research Center Hampton, VA, United States)
Stainback, P. C. (NASA Langley Research Center Hampton, VA, United States)
Srokowski, A. J. (NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)