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Effect of slot width on transition and noise attenuation of a flat sound shield in a mach 6 wind tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Harvey, W. D. Srokowski, A. J. Stainback, P. C. |
| Copyright Year | 1975 |
| Description | An experimental and theoretical study of a sound shield concept to attenuate the noise radiated into the test section from the turbulent boundary layer on the walls of wind tunnels was conducted. The model investigated was planar with a sharp flat plate leading edge faired into an array of rods aligned nearly parallel to the local flow. For a ratio of gap diameter to rod diameter of 0.16, the flow was laminar over the entire model at a maximum local length Reynolds number of 14 million. A 45% reduction in the tunnel free stream root mean square pressure level was measured within the shielded region for this gap width when the boundary layers on the rods were laminar. Smaller ratios of gap diameter to rod diameter resulted in substantial reductions in the transition Reynolds number, and in a 40% pressure reduction. |
| File Size | 2268830 |
| Page Count | 54 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760004023 |
| Archival Resource Key | ark:/13960/t1qg3gr3n |
| Language | English |
| Publisher Date | 1975-11-01 |
| Access Restriction | Open |
| Subject Keyword | Research And Support Facilities (air) Silencers Attenuators Slotted Wind Tunnels Laminar Boundary Layer Flat Plates Noise Reduction Reynolds Number Turbulent Boundary Layer Pressure Reduction Hypersonic Wind Tunnels Boundary Layer Transition Rods Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
