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Investigation Of The Effects Of Nose Bluntness On Natural And Induced Boundary Layer Transition On Axisymmetric Bodies In Supersonic Flow
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Book Synopsis An Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary Layer Transition on Axisymmetric Bodies in Supersonic Flow by : Jack D. Coats
Download or read book An Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary Layer Transition on Axisymmetric Bodies in Supersonic Flow written by Jack D. Coats and published by . This book was released on 1969 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-layer Transition on Axisymmetric Bodies in Supersonic Flow by : Jack D. Coats
Download or read book Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-layer Transition on Axisymmetric Bodies in Supersonic Flow written by Jack D. Coats and published by . This book was released on 1973 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of tests has been conducted at free-stream Mach numbers four and eight to determine the effectiveness of three-dimensional boundary-layer trips in promoting transition on very blunt axisymmetric bodies with near equilibrium wall temperatures. Temperature distributions obtained with temperature sensing gages inserted in the model surface were used to locate boundary-layer transition at Mach number four, and qualitative results, based on pitot pressure measurements, were obtained at Mach number eight. A simple modification of a technique proposed by van Driest and Blummer for determining an effective trip size for blunt bodies is shown to yield a correlation applicable to their data on a sphere at Mach number two and the present configurations at Mach number four.
Book Synopsis Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-Layer Transition on Axisymmetric Bodies in Supersonic Flow by :
Download or read book Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-Layer Transition on Axisymmetric Bodies in Supersonic Flow written by and published by . This book was released on 1973 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of tests has been conducted at free-stream Mach numbers four and eight to determine the effectiveness of three-dimensional boundary-layer trips in promoting transition on very blunt axisymmetric bodies with near equilibrium wall temperatures. Temperature distributions obtained with temperature sensing gages inserted in the model surface were used to locate boundary-layer transition at Mach number four, and qualitative results, based on pitot pressure measurements, were obtained at Mach number eight. A simple modification of a technique proposed by van Driest and Blummer for determining an effective trip size for blunt bodies is shown to yield a correlation applicable to their data on a sphere at Mach number two and the present configurations at Mach number four.
Book Synopsis Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds by : William A. Cassels
Download or read book Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds written by William A. Cassels 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 by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
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 An Experimental Investigation of the Influence of Nose Bluntness on Boundary Layer by : Robert Joseph Zehentner
Download or read book An Experimental Investigation of the Influence of Nose Bluntness on Boundary Layer written by Robert Joseph Zehentner and published by . This book was released on 1982 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Cone Angel, Mach Number, and Nose Blunting on Transition at Supersonic Speeds by : K. R. Czarnecki
Download or read book Effects of Cone Angel, Mach Number, and Nose Blunting on Transition at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effects of a Small Jet of Air Exhausting from the Nose of a Body of Revolution in Supersonic Flow by : Eugene S. Love
Download or read book The Effects of a Small Jet of Air Exhausting from the Nose of a Body of Revolution in Supersonic Flow written by Eugene S. Love and published by . This book was released on 1952 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds by : Gary T. Chapman
Download or read book Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds written by Gary T. Chapman and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Time-dependent Method for Calculating Supersonic Angle-of-attack Flow about Axisymmetric Blunt Bodies with Sharp Shoulders and Smooth Nonaxisymmetric Blunt Bodies by : Richard W. Barnwell
Download or read book A Time-dependent Method for Calculating Supersonic Angle-of-attack Flow about Axisymmetric Blunt Bodies with Sharp Shoulders and Smooth Nonaxisymmetric Blunt Bodies written by Richard W. Barnwell and published by . This book was released on 1971 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A time-dependent numerical method for calculating supersonic flow about blunt bodies at large angles of attack is presented. The axisymmetric bodies with sharp shoulders which are treated are constructed with a generator composed of segments of constant curvature. The nonaxisymmetric bodies have continuous slope and curvature. All flow fields are inviscid and adiabatic and have one plane of symmetry. A modification to the method of characteristics is introduced for use at the shock wave. A two-step finite-difference method of second-order accuracy is used at the body surface and in the region between the shock and body. A new finite-difference technique is introduced for use at sharp sonic shoulders. Comparisons of the results of the present method with experiment and the results of other methods are made for the flow of equilibrium air past the Apollo command module at the trim angle of attack and for perfect gas flow past a spherical cap and a spherically blunted cone at angle of attack. Both the cap and the blunted cone are terminated with sharp shoulders. Results are presented also for perfect gas flow past a prolate spheroid with its major axis normal to the flow.
Book Synopsis A Procedure for the Determination of the Effect of Fuselage Nose Bluntness on the Wave Drag of Supersonic Cruise Aircraft by :
Download or read book A Procedure for the Determination of the Effect of Fuselage Nose Bluntness on the Wave Drag of Supersonic Cruise Aircraft written by and published by . This book was released on 1978 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Supersonic Boundary Layer Transition and Turbulent Structure by : Alexander J. Smits
Download or read book Investigation of Supersonic Boundary Layer Transition and Turbulent Structure written by Alexander J. Smits and published by . This book was released on 1990 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow by : Robert W. Higgins
Download or read book An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow written by Robert W. Higgins and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition has been studied on a heated flat plate in an air stream at a Mach number of 2.40 and a length Reynolds number range from 475,000 to 3,930,000. The transition region was investigated at nominal plate temperature levels of 60, 100, 140, 180, and 260 degrees F and depicted in a series of curves of transition Reynolds numbers, based on boundary-layer dimensions and fluid properties evaluated alternatively at free-stream and wall temperatures. The average skin-friction coefficient over the laminar portion of the boundary layer was determined.
Book Synopsis The Inviscid Stability of Supersonic Flow Past Heated Or Cooled Axisymmetric Bodies by : Institute for Computer Applications in Science and Engineering
Download or read book The Inviscid Stability of Supersonic Flow Past Heated Or Cooled Axisymmetric Bodies written by Institute for Computer Applications in Science and Engineering and published by . This book was released on 1990 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack by : G. Moretti
Download or read book Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack written by G. Moretti and published by . This book was released on 1968 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Comparisons are made between the cylindrical and polar coordinate system used in determining the three-dimensional shock layer flow over the nose region of a blunted supersonic vehicle. Jusfification for the development of a polar coordinate system is given and an outline for such development is presented. Results from the polar coordinate system are given as is the limiting useful range.
Book Synopsis A Method for Determining the Total Drag of a Pointed Body of Revolution in Supersonic Flow with Turbulent Boundary Layer by : Charlie M. Jackson
Download or read book A Method for Determining the Total Drag of a Pointed Body of Revolution in Supersonic Flow with Turbulent Boundary Layer written by Charlie M. Jackson and published by . This book was released on 1969 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow by : Maurice Tucker
Download or read book Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow written by Maurice Tucker and published by . This book was released on 1951 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
