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An Investigation Of Skin Friction Drag In Supersonic Flow Over A Flat Plate With An Electrostatic Charge
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Book Synopsis An Investigation of Skin Friction Drag in Supersonic Flow Over a Flat Plate with an Electrostatic Charge by : Larry J. Harper
Download or read book An Investigation of Skin Friction Drag in Supersonic Flow Over a Flat Plate with an Electrostatic Charge written by Larry J. Harper and published by . This book was released on 1963 with total page 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 An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on Flat Plate at Supersonic Speeds by : Morris W. Rubesin
Download or read book An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on Flat Plate at Supersonic Speeds written by Morris W. Rubesin and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Average skin-friction coefficients have been measured on an insulated flat plate in turbulent flow at a Mach nubmer of 2.5 for a Reynolds number range of 2,100,000 to 6,200,000 and compared with several known existing analyses. The postulates assumed for developing these analyses and the effect of some of the postulates on the average skin-friction coefficient have been shown. It was found that the analysis corresponding more closely to the experimental data for average skin-friction coefficient in the range of 0
Book Synopsis Considerations Regarding the Evaluation and Reduction of Supersonic Skin Friction by : John B. Peterson
Download or read book Considerations Regarding the Evaluation and Reduction of Supersonic Skin Friction written by John B. Peterson and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Problem of Roughness Drag at Supersonic Speeds by : K. R. Czarnecki
Download or read book The Problem of Roughness Drag at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1987 with total page 1126 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis Effects of Surface Emittance on Turbulent Skin Friction at Supersonic and Low Hypersonic Speeds by : Jerry M. Allen
Download or read book Effects of Surface Emittance on Turbulent Skin Friction at Supersonic and Low Hypersonic Speeds written by Jerry M. Allen and published by . This book was released on 1965 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: A search of available literature indicates that the radiative properties of supersonic aircraft materials depend heavily upon the metal chosen for the aircraft skin and the degree of oxidation of the surface. A calculative study has been made to determine the effect of emittance upon wall temperature and skin friction over a range of supersonic and low hypersonic flight conditions. Calculations were made for Mach numbers up to 9, altitudes up to 80 000 feet, and vehicle lengths up to 200 feet. The results indicate that the skin-friction drag of a supersonic aircraft increases with increased surface emittance. Emittance increases with surface oxidation. Thus, for a new supersonic aircraft with skin made of a metal with low radiative properties in the polished, unoxidized state, the skin-friction drag will increase with time until the surface becomes stably oxidized. This effect of emittance on skin friction increases with Mach number and becomes substantial above Mach numbers of about 2.5. Hence, for specified flight conditions, the level of skin-friction drag at which the vehicle operates depends upon the m tal used for the skin of the aircraft and the degree of oxidation of the metal.
Book Synopsis Masters Theses and Doctoral Dissertations in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States by :
Download or read book Masters Theses and Doctoral Dissertations in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States written by and published by . This book was released on 1961 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :United States. National Aeronautics and Space Administration Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :2300 pages Book Rating :4.F/5 ( download)
Book Synopsis NASA Scientific and Technical Reports by : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1967 with total page 2300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1967 with total page 848 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A General Review of Concepts for Reducing Skin Friction, Including Recommendations for Future Studies by : Michael C. Fischer
Download or read book A General Review of Concepts for Reducing Skin Friction, Including Recommendations for Future Studies written by Michael C. Fischer and published by . This book was released on 1974 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Masters Theses in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States by :
Download or read book Masters Theses in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States written by and published by . This book was released on 1966 with total page 446 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag by : August F. Bromm
Download or read book Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag written by August F. Bromm and published by . This book was released on 1956 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 9-inch supersonic tunnel to determine the effect of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag at zero lift of seven boattail bodies of revolution designed for minimum wave drag according to NACA Technical Note 2550. The investigation covered a Reynolds number range from approximately 1,000,000 to 10,000,000 at Mach numbers of 1.62, 1.93, and 2.41, respectively. The results show that base drag and, in general, the total drag increase with increasing values of the ratio of base area to maximum area B/S(max), although the results reported in NACA Technical Note 3054 showed that the wave drag decreased with ticreasing values of B/S(max). The laminar skin-friction drag is in agreement with the theoretical predictions used, and, within the Mach number range of these tests, the simple Blasius incompressible theory gives a satisfactory prediction. Except for values of B/S(max) near 1, the Reynolds number of transition increases with increasing Mach number and, as this ratio approaches 1, this variation is seen to reverse. These variations in Reynolds number of transition with Mach number appear to be associated with the changes in pressure gradient over the rear of the bodies.
Book Synopsis Effects of Leading-edge Blunting on the Local Heat Transfer and Pressure Distributions Over Flat Plates in Supersonic Flow by : Marcus O. Creager
Download or read book Effects of Leading-edge Blunting on the Local Heat Transfer and Pressure Distributions Over Flat Plates in Supersonic Flow written by Marcus O. Creager and published by . This book was released on 1957 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effect of leading-edge thickness on the flow over flat plates with square and cylindrical blunting was conducted at a Mach number of 4 and free-stream Reynolds numbers per inch of 2380 and 6600. Surface pressures were measured on a series of models whose leading-edge thicknesses ranged from 0.25 to 1 inch. Heat-transfer rates were measured from a flat plate which was blunted by a 1-inch-diameter cylindrical leading edge. All tests were performed with the instrumented surfaces at zero angle of sweep and zero angle of attack. For the test condition, the bow shock wave was detached and leading-edge shape had no effect on surface pressures aft of two leading-edge thicknesses. The surface pressures could be predicted by a combination of shock-wave boundary-layer interaction theory and blast wave theory. This combination applied equally well to similar data of other investigations. An empirical expression for local Reynolds number at the boundary-layer edge was found to correlate both the present data and data from other investigations covering a wide range of conditions. The local Reynolds number per inch was found to be lower than free-stream Reynolds number per inch, nearly constant for the test length, and to have negligible dependence on leading-edge bluntness. This reduction depends on the square root of the ratio of total pressures across the normal bow shock wave. The local Nusselt number was found to depend only on the local Reynolds number for the present tests, and is predicted by the familiar Pohlhausen flat-plate theory. As compared to the sharp condition, blunting the leading edge of flat plates, with consequent reduction of local total pressure, was found to increase the heat-transfer coefficients in the region where surface static pressures were high and to reduce the coefficients where the surface static pressures approached the free-stream value.
Book Synopsis Skin Friction Reduction in Supersonic Flow by Injection Through Slots, Porous Sections and Combinations of the Two by : Joseph A. Schetz
Download or read book Skin Friction Reduction in Supersonic Flow by Injection Through Slots, Porous Sections and Combinations of the Two written by Joseph A. Schetz and published by . This book was released on 1975 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Local and Average Skin Friction in the Laminar Boundary Layer on a Flat Plate at a Mach Number of 2.4 by : Randall C. Maydew
Download or read book Experimental Investigation of the Local and Average Skin Friction in the Laminar Boundary Layer on a Flat Plate at a Mach Number of 2.4 written by Randall C. Maydew and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Average and local skin-friction coefficients for laminar flow have been determined experimentally on a flat plate at a Mach number of 2.4 for a Reynolds number range of 720,000 to 2.800,000 and compared with a laminar-boundary-layer theory of Chapman and Rubesin. The average skin-friction data were considerably higher than values predicted by laminar-boundary-layer theory. Local skin-friction coefficients, evaluated by the two methods, agreed well with the theory when plotted against a momentum-thickness Reynolds.
Author :United States. National Aeronautics and Space Administration. Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :258 pages Book Rating :4.E/5 ( download)
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1963 with total page 258 pages. Available in PDF, EPUB and Kindle. Book excerpt:
