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Boundary Layer Velocity Profiles And Skin Friction Due To Surface Roughness On An Ogive Cylinder At Mach Numbers Of 161 And 201
Download Boundary Layer Velocity Profiles And Skin Friction Due To Surface Roughness On An Ogive Cylinder At Mach Numbers Of 161 And 201 full books in PDF, epub, and Kindle. Read online Boundary Layer Velocity Profiles And Skin Friction Due To Surface Roughness On An Ogive Cylinder At Mach Numbers Of 161 And 201 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Boundary-layer Velocity Profiles and Skin Friction Due to Surface Roughness on an Ogive Cylinder at Mach Numbers of 1.61 and 2.01 by : K. R. Czarnecki
Download or read book Boundary-layer Velocity Profiles and Skin Friction Due to Surface Roughness on an Ogive Cylinder at Mach Numbers of 1.61 and 2.01 written by K. R. Czarnecki and published by . This book was released on 1963 with total page 54 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 Compressible Turbulent Skin Friction on Rough and Rough/wavy Walls in Adiabatic Flow by : Daniel C. Reda
Download or read book Compressible Turbulent Skin Friction on Rough and Rough/wavy Walls in Adiabatic Flow written by Daniel C. Reda and published by . This book was released on 1974 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to investigate effects of roughness, and roughness superimposed on single and/or multiple, shallow, periodic waveforms, on turbulent boundary-layer skin friction and velocity profile, in compressible, adiabatic flow. Test conditions were Mach number = 2.9 and Reynolds number/ft = 2 million to 8 million. The planar models included smooth, sand-grain, machined and molded surface finishes. Direct measurements of surface shear and Pitot/recovery temperature profiles were obtained. (Modified author abstract).
Book Synopsis Pressure Distributions and Wave Drag Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder at Mach Numbers of 1.61 and 2.01 by : K. R. Czarnecki
Download or read book Pressure Distributions and Wave Drag Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder at Mach Numbers of 1.61 and 2.01 written by K. R. Czarnecki and published by . This book was released on 1961 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Roughness Drag Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder from Force Tests at Transonic Speeds by : K. R. Czarnecki
Download or read book Roughness Drag Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder from Force Tests at Transonic Speeds written by K. R. Czarnecki and published by . This book was released on 1969 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 The Characteristics of a Laminar Boundary Layer on a Spinning Tangent Ogive Cylinder at Angle of Attack by : H. R. Vaughn
Download or read book The Characteristics of a Laminar Boundary Layer on a Spinning Tangent Ogive Cylinder at Angle of Attack written by H. R. Vaughn and published by . This book was released on 1972 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Streamwise velocity profiles of a laminar boundary layer were determined from pitot pressure measurements made in a supersonic wind tunnel on a spinning tangent ogive cylinder at zero and four degrees angle of attack. A transformation was found which transforms the velocity profiles to be in agreement with the incompressible Blasius profile.
Book Synopsis Boundary Layer Effects by : Anthony W. Fiore
Download or read book Boundary Layer Effects written by Anthony W. Fiore and published by . This book was released on 1978 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.
Book Synopsis Design and Evaluation of a New Boundary-layer Rake for Flight Testing by : Trong T. Bui
Download or read book Design and Evaluation of a New Boundary-layer Rake for Flight Testing written by Trong T. Bui and published by . This book was released on 2000 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new boundary-layer rake has been designed and built for flight testing on the NASA Dryden Flight Research Center F-15B/Flight Test Fixture. A feature unique to this rake is its curved body, which allows pitot tubes to be more densely clustered in the near-wall region than conventional rakes allow. This curved rake design has a complex three-dimensional shape that requires innovative solid-modeling and machining techniques. Finite-element stress analysis of the new design shows high factors of safety. The rake has passed a ground test in which random vibration measuring 12 g rms was applied for 20 min in each of the three normal directions. Aerodynamic evaluation of the rake has been conducted in the NASA Glenn Research Center 8x6 Supersonic Wind Tunnel at Mach 0-2. The pitiot pressures from the new rake agree with conventional rake data over the range of Mach numbers tested. The boundary-layer profiles computed from the rake data have been shown to have the standard logarithmic-law profile. Skin friction values computed from the rake data using the Clauser plot method agree with the Preston tube results and the van Driest II compressible skin friction correlation to approximately plus/minus 5 percent.
Book Synopsis A Real-time Method for Estimating Viscous Forebody Drag Coefficients by : Stephen A. Whitmore
Download or read book A Real-time Method for Estimating Viscous Forebody Drag Coefficients written by Stephen A. Whitmore and published by . This book was released on 2000 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper develops a real-time method based on the law of the wake for estimating forebody skin-friction coefficients. The incompressible law-of-the-wake equations are numerically integrated across the boundary layer depth to develop an engineering model that relates longitudinally averaged skin-friction coefficients to local boundary layer thickness. Solutions applicable to smooth surfaces with pressure gradients and rough surfaces with negligible pressure gradients are presented. Model accuracy is evaluated by comparing model predictions with previously measured flight data. This integral law procedure is beneficial in that skin-friction coefficients can be indirectly evaluated in real-time using a single boundary layer height measurement. In this concept a reference pitot probe is inserted into the flow, well above the anticipated maximum thickness of the local boundary layer. Another probe is servomechanism-driven and floats within the boundary layer. A controller regulates the position of the floating probe. The measured servomechanism of this second probe provides an indirect measurement of both local and longitudinally averaged skin friction. Simulation results showing the performance of the control law for a noisy boundary layer are then presented.
Book Synopsis Viscous Drag Reduction in Boundary Layers by :
Download or read book Viscous Drag Reduction in Boundary Layers written by and published by AIAA. This book was released on 1990 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Influence of Surface Roughness on Supersonic High Reynolds Number Turbulent Boundary Layer Flow by : Robert M. Latin
Download or read book The Influence of Surface Roughness on Supersonic High Reynolds Number Turbulent Boundary Layer Flow written by Robert M. Latin and published by . This book was released on 1998-03-01 with total page 362 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive study of rough-wall high speed (M=2.9) high Reynolds number (Re/m = 1.9. 10 to the 7th power) turbulent boundary layer flow was performed consisting of experimental, analytical, and numerical methods. Six wall topologies consisting of a smooth and five rough surfaces (two and three dimensional machined roughness plates; and 80, 36, and 20 grit sand-grain roughened plates) were studied. A confocal laser scan microscope was used to measure the topography of the sand grain roughnesses. The experimental measurement techniques included a convention Pitot pressure probe, laser Doppler velocimetry, hot wire anemometry; color schlieren and laser sheet Mie scattering images. Mean measurements included velocity, Mach number, density, and mass flux. Turbulent measurements included velocity and mass flux turbulence intensities, kinematic Reynolds shear stress, compressible Reynolds shear stress in two planes, and the traverse apparent mass flux. Kinematic turbulent flow statistical properties were found to scale by local mean quantities and displayed a weak dependence on surface roughness. Turbulent flow statistical properties with the explicit appearance of density did not scale by local mean quantities, and had a strong linear dependence on roughness. Surface roughness also had a significant effect on the flow structure size, angles, and energy spectra. A theoretical analysis was performed and a new integral method for the estimation of skin friction was developed. The skin friction estimates were within 4% of compressible semi-empirical relations. A numerical study was performed which used a parabolized Navier Stokes solver with two algebraic turbulence models and the Rotta model for surface roughness. A new method for the estimation of momentum loss improved the numerical flow predictability.
Book Synopsis Skin Friction Reduction by Slot Injection at Mach 0.8 by : Victor Zakkay
Download or read book Skin Friction Reduction by Slot Injection at Mach 0.8 written by Victor Zakkay and published by . This book was released on 1976 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Drags Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder at Transonic Speeds by : K. R. Czarnecki
Download or read book Pressure Drags Due to Two-dimensional Fabrication-type Surface Roughness on an Ogive Cylinder at Transonic Speeds written by K. R. Czarnecki and published by . This book was released on 1966 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Skin Friction Intwo-dimensional, Transonic, Turbulent Flow by : T. W. Swafford
Download or read book Calculation of Skin Friction Intwo-dimensional, Transonic, Turbulent Flow written by T. W. Swafford and published by . This book was released on 1979 with total page 54 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:
