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Skin Friction Measurements At A Mach Number Of Three And Momentum Thickness Reynolds Numbers Up To A Half Million
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Book Synopsis Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million by : Anthony W. Fiore
Download or read book Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million written by Anthony W. Fiore and published by . This book was released on 1980 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Surface shear stress measurements were made in the Flight Dynamics Laboratory's M=3 High Reynolds Number wind tunnel. The primary purpose of this research was to make shear stress measurements at very high Reynolds numbers for near adiabatic wall and zero pressure gradient conditions. The results are presented as the local skin friction coefficient versus both the momentum thickness and the length Reynolds number. The investigation was conducted on the nozzle wall at a nominal Mach number of three over the Reynolds number range of 20,000
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 1981 with total page 788 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 1978 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Skin-friction Measurements in Incompressible Flow by : Donald W. Smith
Download or read book Skin-friction Measurements in Incompressible Flow written by Donald W. Smith and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiment have been conducted to measure the local surface-shear stress and the average skin-friction coefficient in incompressible flow for a turbulent boundary layer on a smooth flat plate having zero pressure gradient. Data were obtained for a range of Reynolds numbers from 1 million to 45 million. The local surface-shear stress was measured by a floating-element skin-friction balance and also by a calibrated total head tube located on the surface of the test wall. The average skin-friction coefficient was obtained from boundary-layer velocity profiles.
Book Synopsis Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers in Air and Helium by : Fred W. Matting
Download or read book Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers in Air and Helium written by Fred W. Matting and published by . This book was released on 1961 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers in Air and Helium by : Fred W. Matting
Download or read book Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers in Air and Helium written by Fred W. Matting and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are given of local skin-friction measurements in turbulent boundary layers over an equivalent air Mach number range from 0.2 to 9.9 and an over-all Reynolds number variation of 2x106 to 100x106. Direct force measurements were made by means of a floating element. Flows were two-dimensional over a smooth flat surface with essentially zero pressure gradient and with adiabatic conditions at the wall. Air and helium were used as working fluids. An equivalence parameter for comparing boundary layers in different working fluids is derived and the experimental verification of the parameter is demonstrated. Experimental results are compared with the resuls obtained by several methods of calculating skin friction in the turbulent boundary layer.
Book Synopsis Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy by : Alvin Seiff
Download or read book Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy written by Alvin Seiff and published by . This book was released on 1954 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer data from four wind-tunnel experiments and two free-flight experiments with turbulent boundary layers have been examined to see whether or not they are well represented by the Reynolds analogy or a modification thereof. The heat-transfer results are put into the form of dimensionless Stanton numbers based on fluid properties at the outer edge of the boundary layer and are compared with skin-friction coefficients for the same Mach numbers and wall to free-stream temperature ratios as obtained from an interpolation of the existing skin-friction data. The effective Reynolds number is taken to be the length Reynolds number measured from the effective turbulent origin, a position which differs importantly from the leading edge of the test surface in some cases.
Book Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 1078 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis R & D Abstracts by : Technology Reports Centre (Great Britain)
Download or read book R & D Abstracts written by Technology Reports Centre (Great Britain) and published by . This book was released on 1981 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1972 with total page 520 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Turbulent Boundary-layer Measurements Obtained from the Forebody of an Airplane at Mach Numbers Up to 1.72 by : Edwin J. Saltzman
Download or read book Some Turbulent Boundary-layer Measurements Obtained from the Forebody of an Airplane at Mach Numbers Up to 1.72 written by Edwin J. Saltzman and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Direct Measurements of Turbulent Skin Friction on a Nonadiabatic Flat Plate at Mach Number 6.5 and Comparisons with Eight Theories by : Edward J. Hopkins
Download or read book Direct Measurements of Turbulent Skin Friction on a Nonadiabatic Flat Plate at Mach Number 6.5 and Comparisons with Eight Theories written by Edward J. Hopkins and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1981 with total page 942 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical Study of Soft Landings on Gas-filled Bags by : Jack B. Esgar
Download or read book Analytical Study of Soft Landings on Gas-filled Bags written by Jack B. Esgar and published by . This book was released on 1960 with total page 732 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Report written by and published by . This book was released on 1961 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Method for Measuring the Product of Inertia and the Inclination of the Principal Longitudinal Axis of Inertia of an Airplane by : Robert W. Boucher
Download or read book A Method for Measuring the Product of Inertia and the Inclination of the Principal Longitudinal Axis of Inertia of an Airplane written by Robert W. Boucher and published by . This book was released on 1954 with total page 718 pages. Available in PDF, EPUB and Kindle. Book excerpt: The angle of inclination of the principal axis was found to have probable error of plus or minus 0.17 degrees both from analysis of the error of inertia measurement of the full-scale airplane and from tests with a model having a simple configuration. Analysis showed the probable error of the inertia measurements for the test airplane to be plus or minus1.00, plus or minus 0.49, and plus or minus 0.35 percent of the true moment of inertia about the X, Y, and Z body reference axes, respectively.
Download or read book NASA Technical Note written by and published by . This book was released on 1970 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
