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Effects Of Radiated Aerodynamic Noise On Model Boundary Layer Transition In Supersonic And Hypersonic Wind Tunnels
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Book Synopsis Effects of Radiated Aerodynamic Noise on Model Boundary-layer Transition in Supersonic and Hypersonic Wind Tunnels by : S. R. Pate
Download or read book Effects of Radiated Aerodynamic Noise on Model Boundary-layer Transition in Supersonic and Hypersonic Wind Tunnels written by S. R. Pate and published by . This book was released on 1968 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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
Book Synopsis Dominance of Radiated Aerodynamic Noise on Boundary-layer Transition in Supersonic-hypersonic Wind Tunnels by : Samuel R. Pate
Download or read book Dominance of Radiated Aerodynamic Noise on Boundary-layer Transition in Supersonic-hypersonic Wind Tunnels written by Samuel R. Pate and published by . This book was released on 1978 with total page 418 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis An Investigation of Radiated Aerodynamic Noise Effects on Boundary-layer Transition in Supersonic and Hypersonic Wind Tunnels by : S. R. Pate
Download or read book An Investigation of Radiated Aerodynamic Noise Effects on Boundary-layer Transition in Supersonic and Hypersonic Wind Tunnels written by S. R. Pate and published by . This book was released on 1968 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Dominance of Radiated Aerodynamic Noise on Boundary-layer Transition in Supersonic-hypersonic Wind Tunnels by : Samuel Ralph Pate
Download or read book Dominance of Radiated Aerodynamic Noise on Boundary-layer Transition in Supersonic-hypersonic Wind Tunnels written by Samuel Ralph Pate and published by . This book was released on 1977 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Boundary-layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality by : N. Sam Dougherty
Download or read book Boundary-layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality written by N. Sam Dougherty and published by . This book was released on 1982 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition location measurements were made on a 10-deg sharp cone in 23 wind tunnels in the United States and Europe and in flight. The data were acquired at subsonic, transonic, and supersonic Mach numbers over a range of unit Reynolds numbers in an effort to obtain an improved understanding of the effect of wind tunnel flow quality on transition location. The data indicate that the transition mechanism in both wind tunnels and flight is associated with the formation of Tollmien-Schlichting waves in the laminar boundary layer. However, the location of the end of transition was found to be primarily a function of the noise under the laminar boundary of the cone surface and, within + or - 20 percent, independent of Mach number and unit Reynolds number. (Author).
Book Synopsis Influence of Free-stream Disturbances on Boundary-layer Transition by : Bill Harvey
Download or read book Influence of Free-stream Disturbances on Boundary-layer Transition written by Bill Harvey and published by . This book was released on 1978 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary Layer Transition at Supersonic Speeds by : E. R. Van Driest
Download or read book Boundary Layer Transition at Supersonic Speeds written by E. R. Van Driest and published by . This book was released on 1961 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Effects of Wall Cooling and Leading-edge Blunting on Ramp-induced, Laminar Flow Separations at Mach Numbers from 3 Through 6 by : J. Don Gray
Download or read book Effects of Wall Cooling and Leading-edge Blunting on Ramp-induced, Laminar Flow Separations at Mach Numbers from 3 Through 6 written by J. Don Gray and published by . This book was released on 1972 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of wall cooling and nose bluntness on laminar and transitional reattaching flows induced by a 9.5-degree ramp were investigated at Mach numbers from 3 through 6 measuring the longitudinal surface pressure and heat-transfer rate distributions, as well as the flow-field pressures, at several longitudinal stations. Reynolds number based on flat-plate length was varied from 0.25 to 1.0 million. The trend in the change in interaction length with Reynolds number increase indicated laminar reattachment at all test Reynolds numbers at M = 6 and transitional at the two higher Reynolds numbers at M = 3.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Flow-field Tests of the McDonnell Douglas-Martin Marietta Space Shuttle Configurations by : Richard K. Matthews
Download or read book Heat-transfer and Flow-field Tests of the McDonnell Douglas-Martin Marietta Space Shuttle Configurations written by Richard K. Matthews and published by . This book was released on 1973 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerothermodynamic tests of Phase B space shuttle configurations proposed by McDonnell Douglas--Martin Marietta were conducted at Mach numbers 8 and 10.5. Test conditions provided both Mach number and Reynolds number simulation for typical ascent and reentry trajectories. This report provides a comprehensive analysis of the major test results and also presents data comparisons with theoretical calculations. Specific areas covered are ascent heating and shock interference, booster reentry heating and flow fields, and orbiter reentry analysis which includes leeside heating, windward shock angles and flow fields, windward surface heating, and boundary-layer transition.
Book Synopsis Interaction of Aerodynamic Noise with Laminar Boundary Layers in Supersonic Wind Tunnels by : M. R. Schopper
Download or read book Interaction of Aerodynamic Noise with Laminar Boundary Layers in Supersonic Wind Tunnels written by M. R. Schopper and published by . This book was released on 1984 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Influence of Free-stream Disturbances on Boundary-layer Transition by : William D. Harvey
Download or read book Influence of Free-stream Disturbances on Boundary-layer Transition written by William D. Harvey and published by . This book was released on 1978 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1975 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comments on Hypersonic Boundary-layer Transition by : Kenneth F. Stetson
Download or read book Comments on Hypersonic Boundary-layer Transition written by Kenneth F. Stetson and published by . This book was released on 1990 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis NASA Technical Paper by : United States. National Aeronautics and Space Administration
Download or read book NASA Technical Paper written by United States. National Aeronautics and Space Administration and published by . This book was released on 1977 with total page 964 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Publisher : ISBN 13 : Total Pages :176 pages Book Rating :4.3/5 (243 download)
Book Synopsis AGARD Advisory Report by : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Download or read book AGARD Advisory Report written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development and published by . This book was released on 1998 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1983 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
