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Influence Of Wind Tunnel Noise On The Location Of Boundary Layer Transition On A Slender Cone At Mach Numbers From 02 To 55
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Book Synopsis Influence of Wind Tunnel Noise on the Location of Boundary-layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5 by : N. Sam Dougherty (Jr.)
Download or read book Influence of Wind Tunnel Noise on the Location of Boundary-layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5 written by N. Sam Dougherty (Jr.) and published by . This book was released on 1980 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study was conducted to investigate the effects of wind tunnel test section noise on the location of boundary-layer transition. The study was carried out by conducting experiments on a slender, highly polished cone with an included angle of 10 deg. Wind tunnel test section noise was measured by microphones flush-mounted on the cone surface. In most of the experiments, boundary-layer transition was measured with a surface-mounted, traversing pitot pressure probe. The experiments were conducted in 23 different subsonic, transonic, and supersonic wind tunnels over a Mach number range from 0.2 to 5.5 and a unit Reynolds number range from 1.0 to 7.0 million per foot, the bulk of the data being obtained between 2.0 and 4.0 million per foot. The results show an influence of wind tunnel noise on boundary-layer transition for most of the wind tunnels. (Author)
Book Synopsis Influence of Wind Tunnel Noise on the Location of Boundary-layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5 by : N. Sam Dougherty
Download or read book Influence of Wind Tunnel Noise on the Location of Boundary-layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5 written by N. Sam Dougherty and published by . This book was released on 1980 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study was conducted to investigate the effects of wind tunnel noise on the location of boundary-layer transition. The study was carried out by conducting experiments on a particular slender, highly polished cone having an included angle of 10 deg. Wind tunnel noise levels were measured in the test section by flush-mounted microphones imbedded in the cone surface. The measurement of boundary-layer transition location was made using either a traversing pitot pressure probe in contact with the cone surface or the flush-mounted microphones. The experiments were carried out in 23 different subsonic, transonic, and supersonic wind tunnels over a range of Mach numbers from 0.2 to 5.5 and a unit Reynolds number range from 1.0 to 7.0 million per foot, the bulk of the data being obtained for a range from 2.0 to 4.0 million per foot. The results clearly show a strong influence of wind tunnel noise on boundary-layer transition location correlatable with overall root-mean-square noise levels. Because the noise level generally varied with Mach number and unit Reynolds number, the unit Reynolds number was found to have little effect on transition Reynolds number. (Author).
Book Synopsis Influence of Wind Tunnel Noise on the Location of Boundary-Layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5. Volume II. Tabulated and Plotted Data by : N. Sam Dougherty (Jr)
Download or read book Influence of Wind Tunnel Noise on the Location of Boundary-Layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5. Volume II. Tabulated and Plotted Data written by N. Sam Dougherty (Jr) and published by . This book was released on 1980 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study was conducted to investigate the effects of wind tunnel test section noise on the location of boundary-layer transition. The study was carried out by conducting experiments on a slender, highly polished cone with an included angle of 10 deg. Wind tunnel test section noise was measured by microphones flush-mounted on the cone surface. In most of the experiments, boundary-layer transition was measured with a surface-mounted, traversing pitot pressure probe. The experiments were conducted in 23 different subsonic, transonic, and supersonic wind tunnels over a Mach number range from 0.2 to 5.5 and a unit Reynolds number range from 1.0 to 7.0 million per foot, the bulk of the data being obtained between 2.0 and 4.0 million per foot. The results show an influence of wind tunnel noise on boundary-layer transition for most of the wind tunnels. (Author).
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 Wind Tunnel Noise on the Location of Boundary-Layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5. Volume I. Experimental Methods and Summary of Results by : N. Sam Dougherty (Jr)
Download or read book Influence of Wind Tunnel Noise on the Location of Boundary-Layer Transition on a Slender Cone at Mach Numbers from 0.2 to 5.5. Volume I. Experimental Methods and Summary of Results written by N. Sam Dougherty (Jr) and published by . This book was released on 1980 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study was conducted to investigate the effects of wind tunnel noise on the location of boundary-layer transition. The study was carried out by conducting experiments on a particular slender, highly polished cone having an included angle of 10 deg. Wind tunnel noise levels were measured in the test section by flush-mounted microphones imbedded in the cone surface. The measurement of boundary-layer transition location was made using either a traversing pitot pressure probe in contact with the cone surface or the flush-mounted microphones. The experiments were carried out in 23 different subsonic, transonic, and supersonic wind tunnels over a range of Mach numbers from 0.2 to 5.5 and a unit Reynolds number range from 1.0 to 7.0 million per foot, the bulk of the data being obtained for a range from 2.0 to 4.0 million per foot. The results clearly show a strong influence of wind tunnel noise on boundary-layer transition location correlatable with overall root-mean-square noise levels. Because the noise level generally varied with Mach number and unit Reynolds number, the unit Reynolds number was found to have little effect on transition Reynolds number. (Author).
Book Synopsis Boundary-Layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality by :
Download or read book Boundary-Layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality written by and published by . This book was released on 1982 with total page 0 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 Boundary-Layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality by : N. Sam Dougherty (Jr)
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 (Jr) and published by . This book was released on 1982 with total page 49 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 Boundary-layer Transition on Cones Near Mach One in an Aeroballistic Range by : J. Leith Potter
Download or read book Boundary-layer Transition on Cones Near Mach One in an Aeroballistic Range written by J. Leith Potter and published by . This book was released on 1975 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or
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 1992 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Correlation of Artifically Induced Boundary-layer Transition Data from Blunt Slender Cones at Hypersonic Speeds by : Albert H. Boudreau
Download or read book A Correlation of Artifically Induced Boundary-layer Transition Data from Blunt Slender Cones at Hypersonic Speeds written by Albert H. Boudreau and published by . This book was released on 1979 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-stream Noise and Transition Measurements on a Cone in a Mach 3.5 Pilot Low-disturbance Tunnel by :
Download or read book Free-stream Noise and Transition Measurements on a Cone in a Mach 3.5 Pilot Low-disturbance Tunnel written by and published by . This book was released on 1983 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of a Modified Leading Edge on Noise and Boundary-layer Transition in a Rod-wall Sound Shield at Mach 5 by : Theodore R. Creel
Download or read book Effects of a Modified Leading Edge on Noise and Boundary-layer Transition in a Rod-wall Sound Shield at Mach 5 written by Theodore R. Creel and published by . This book was released on 1981 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Fluctuating Static Pressure Measurements in the National Transonic Facility by : William B. Igoe
Download or read book Analysis of Fluctuating Static Pressure Measurements in the National Transonic Facility written by William B. Igoe and published by . This book was released on 1996 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 by : Michael C. Fischer
Download or read book An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 written by Michael C. Fischer and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer transition on nose cones at hypersonic speeds.
Book Synopsis Boundary Layer Transition on Slender Cones in Conventional and Low Disturbance Mach 6 Wind Tunnels by : Thomas J. Horvath
Download or read book Boundary Layer Transition on Slender Cones in Conventional and Low Disturbance Mach 6 Wind Tunnels written by Thomas J. Horvath and published by . This book was released on 2002 with total page 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 Noise Reduction in a Mach 5 Wind Tunnel with a Rectangular Rod-wall Sound Shield by :
Download or read book Noise Reduction in a Mach 5 Wind Tunnel with a Rectangular Rod-wall Sound Shield written by and published by . This book was released on 1980 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
