Download or read book Use of Barotoni Libby Transformation and Preston Tube Calibrations to Determine Skin Friction from Turbulent Velocity Profiles written by Jerry Allen and published by . This book was released on 1968 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Calculation of Laminar Skin Friction on a Porous Plate by a Refined Integral Method written by Tse-Fou Zien and published by . This book was released on 1970 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The skin friction on a porous flat plate in the presence of an incompressible laminar boundary layer is calculated by a generalization of a refined integral technique. This method is based on a double integration of the momentum equation, replacing the skin-friction term by an integral representation involving the assumed velocity profile. Both a case of similarity blowing of suction and a case of uniform blowing or suction were studied. Using two simple and crude velocity profiles of polynominal form with constant coefficients, closed-form solutions are obtained through simple procedures and compared with the available exact solutions. The same profiles are then employed in the usual integral method to calculate the corresponding skin friction. (Author).
Download or read book Reevaluation of Compressible Flow Preston Tube Calibrations written by National Aeronautics and Space Administration NASA and published by . This book was released on 2018-09 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Revised zero-pressure-gradient, adiabatic wall skin-friction-balance data covering a Mach number range from 1.6 to 4.6 led to a reevaluation of existing compressible flow Preston tube calibration equations. Allen, J. M. Langley Research Center NASA-TM-X-3488, L-11189 RTOP 505-11-15-02
Download or read book Reevaluation of Compressible Flow Preston Tube Calibrations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-20 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Revised zero-pressure-gradient, adiabatic wall skin-friction-balance data covering a Mach number range from 1.6 to 4.6 led to a reevaluation of existing compressible flow Preston tube calibration equations. Allen, J. M. Langley Research Center NASA-TM-X-3488, L-11189 RTOP 505-11-15-02
Download or read book Balance for Measuring Skin Friction in the Presence of Ablation written by James R. Bruno and published by . This book was released on 1968 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a skin-friction balance that is presently being used to measure shear stresses acting on the wall of an ablative duct. Tests have been conducted in the 3 Megawatt Arc Tunnel with a Mach number of 3, a stagnation enthalpy of 3000 BTU/lb, and a stagnation pressure of 20 atmospheres. The balance is a direct deflection measuring device in that balance arm rotation is measured with a linear variable differential transformer as the balance arm deflects due to shear loads acting on the end of the balance arm. (Author).
Download or read book Exploratory Investigation on the Measurement of Skin Friction by Means of Liquid Crystals written by Enrique J. Klein and published by . This book was released on 1969 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Drag Reduction of Turbulent Flows by Additives written by A. Gyr and published by Springer Science & Business Media. This book was released on 2013-03-09 with total page 243 pages. Available in PDF, EPUB and Kindle. Book excerpt: Drag Reduction of Turbulent Flows by Additives is the first treatment of the subject in book form. The treatment is extremely broad, ranging from physicochemical to hydromechanical aspects. The book shows how fibres, polymer molecules or surfactants at very dilute concentrations can reduce the drag of turbulent flow, leading to energy savings. The dilute solutions are considered in terms of the physical chemistry and rheology, and the properties of turbulent flows are presented in sufficient detail to explain the various interaction mechanisms. Audience: Those active in fundamental research on turbulence and those seeking to apply the effects described. Fluid mechanical engineers, rheologists, those interested in energy saving methods, or in any other application in which the flow rate in turbulent flow should be increased.
Download or read book Skin Friction of Incompressible Turbulent Boundary Layers Under Adverse Pressure Gradients written by Fabio R. Goldschmied and published by . This book was released on 1951 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data for skin friction of turbulent boundary layers under adverse pressure gradient are presented from several sources. Data obtained by momentum balance are shown to follow a trend opposite to that of data obtained by a hot-wire and heat-transfer methods. A new integral energy parameter and a new momentum thickness are introduced. The momentum equation and total-head measuring techniques are discussed in relation to skin-friction computation.
Download or read book Heat Transfer and Skin Friction for Turbulent Boundary Layers on Heated Or Cooled Surfaces at High Speeds written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Download or read book High Accuracy Determination of Skin Friction Differences in an Air Channel Flow Based on Pressure Drop Measurements written by Andreas Güttler and published by Saint Philip Street Press. This book was released on 2020-10-09 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: The present work delivers a versatile, accurate and reliable wind tunnel facility that is particularly developed to test different flow control techniques for drag reduction in precisely adjustable test conditions. Skin friction changes of 0.4% are resolved, which is comparable to the most accurate reported studies in liquids. this high accuracy is verified through a comprehensive uncertainty analysis. Subsequently, various passive and active flow control strategies are investigated. This work was published by Saint Philip Street Press pursuant to a Creative Commons license permitting commercial use. All rights not granted by the work's license are retained by the author or authors.
Download or read book Skin Friction at Very High Reynolds Numbers in the National Transonic Facility written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: Skin friction coefficients were derived from measurements using standard measurement technologies on an axisymmetric cylinder in the NASA Langley National Transonic Facility (NTF) at Mach numbers from 0.2 to 0.85. The pressure gradient was nominally zero, the wall temperature was nominally adiabatic, and the ratio of boundary layer thickness to model diameter within the measurement region was 0.10 to 0.14, varying with distance along the model. Reynolds numbers based on momentum thicknesses ranged from 37,000 to 605,000. The measurements approximately doubled the range of available data for flat plate skin friction coefficients. Three different techniques were used to measure surface shear. The maximum error of Preston tube measurements was estimated to be 2.5 percent, while that of Clauser derived measurements was estimated to be approximately 5 percent. Direct measurements by skin friction balance proved to be subject to large errors and were not considered reliable. Watson, Ralph D. and Anders, John B. and Hall, Robert M. Langley Research Center WBS 759-07-03
