Dominance Of Radiated Aerodynamic Noise On Boundary Layer Transition In Supersonic Hypersonic Wind Tunnels
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Author | : Samuel Ralph Pate |
Publisher | : |
Total Pages | : 0 |
Release | : 1977 |
Genre | : Aerodynamic noise |
ISBN | : |
An experimental investigation was conducted to determine the effects of radiated aerodynamic-noise on boundary-layer transition in supersonic-hypersonic wind tunnels. It is conclusively shown that the aerodynamic noise (pressure fluctuations associated with sound waves), which radiate from the tunnel wall, turbulent boundary layer, will dominate the transition process on sharp flat places and sharp slender cones at zero incidence.
Author | : Samuel Ralph Pate |
Publisher | : |
Total Pages | : 0 |
Release | : 1977 |
Genre | : Aerodynamic noise |
ISBN | : |
An experimental investigation was conducted to determine the effects of radiated aerodynamic-noise on boundary-layer transition in supersonic-hypersonic wind tunnels. It is conclusively shown that the aerodynamic noise (pressure fluctuations associated with sound waves), which radiate from the tunnel wall, turbulent boundary layer, will dominate the transition process on sharp flat places and sharp slender cones at zero incidence.
Author | : S. R. Pate |
Publisher | : |
Total Pages | : 94 |
Release | : 1968 |
Genre | : |
ISBN | : |
Boundary-layer transition and aerodynamic noise measurements were made on sharp leading-edge two-dimensional models in supersonic wind tunnels (1 ft to 16 ft). These data showed, conclusively, a significant and continuous increase in transition Reynolds number and a significant decrease in radiated aerodynamic noise (generated by the tunnel wall turbulent boundary layer) with increasing tunnel size. Results obtained in the AEDC-VKF Tunnel A from a shroud configuration placed concentrically around a hollow cylinder transition model and a flat plate microphone model further demonstrated the strong adverse effects that radiated aerodynamic noise will have on transition. A correlation of transition Reynolds numbers based on transition data from nine wind tunnels (3
Author | : S. R. Pate |
Publisher | : |
Total Pages | : 14 |
Release | : 1968 |
Genre | : Aerodynamic noise |
ISBN | : |
Author | : Samuel R. Pate |
Publisher | : |
Total Pages | : 418 |
Release | : 1978 |
Genre | : Aerodynamic noise |
ISBN | : |
An experimental investigation was conducted to determine the effects of radiated aerodynamic-noise on boundary-layer transition in supersonic-hypersonic wind tunnels. It is conclusively shown that the aerodynamic noise (pressure fluctuations associated with sound waves), which radiate from the tunnel wall, turbulent boundary layer, will dominate the transition process on sharp flat places and sharp slender cones at zero incidence.
Author | : M. R. Schopper |
Publisher | : |
Total Pages | : 176 |
Release | : 1984 |
Genre | : Aerodynamic noise |
ISBN | : |
Author | : E. R. Van Driest |
Publisher | : |
Total Pages | : 108 |
Release | : 1961 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
Author | : |
Publisher | : |
Total Pages | : 492 |
Release | : 1983 |
Genre | : Astronautics |
ISBN | : |
Author | : Fang-Jenq Chen |
Publisher | : |
Total Pages | : 60 |
Release | : 1984 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Kenneth F. Stetson |
Publisher | : |
Total Pages | : 116 |
Release | : 1990 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.