论文信息 - Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel

Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel

An investigation at Mach 3.5 into the effects of nozzle wall roughness on free stream pressure fluctuations and cone transition Reynolds numbers was conducted in the pilot low disturbance tunnel at the Langley Research Center. Nozzle wall roughness caused by either particle deposits or imperfections in surface finish increased free stream noise levels and reduced the transition Reynolds numbers on a cone mounted in the test rhombus.

I. E. Beckwith | T. R. Creel | F. J. Chen | F. Chen

[1] I. E. Beckwith,et al. Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel , 1983 .

[2] I. E. Beckwith,et al. Mean flow and noise measurements in a Mach 3.5 pilot quiet tunnel , 1982 .

[3] E. R. V. Driest,et al. Experiments on Boundary-Layer Transition at Supersonic Speeds , 1957 .

[4] Samuel R. Pate. Effects of Wind Tunnel Disturbances on Boundary-Layer Transition with Emphasis on Radiated Noise: A Review , 1980 .

[5] I. E. Beckwith,et al. Free stream noise and transition measurements in a Mach 3.5 pilot quiet tunnel , 1983 .

[6] I. E. Beckwith. Comments on settling chamber design for quiet, blowdown wind tunnels , 1981 .

[7] L. Kovasznay. Turbulence in Supersonic Flow , 1953 .

[8] R. D. Wagner,et al. A comparison of disturbance levels measured in hypersonic tunnels using a hot-wire anemometer and a pitot pressure probe. , 1972 .