Download or read book Study of Surface Pitots for Measuring Turbulent Skin Friction at Supersonic Mach Numbers written by Edward J. Hopkins and published by . This book was released on 1966 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Use of Preston Tubes for Measuring Hypersonic Turbulent Skin Friction written by Earl R. Keener and published by . This book was released on 1969 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Use of Preston tubes for measuring hypersonic turbulent skin friction.
Download or read book An Experimental Investigation of the Surface Pitot Probe Including Effects of Heat Transfer and Compressibility written by David L. Brott and published by . This book was released on 1968 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the experimental investigation of surface Pitot probe in both subsonic and supersonic flow. The effect of heat transfer on the results was also investigated in supersonic flow. (Author).
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
Download or read book Flight Demonstration of a Skin friction Gage to a Local Mach Number of 4 9 written by Darwin J. Garringer and published by . This book was released on 1967 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pitot probe Displacement in a Supersonic Turbulent Boundary Layer written by Jerry M. Allen and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Eight circular pitot probes ranging in size from 2 to 70 percent of the boundary-layer thickness were tested to provide experimental probe displacement results in a two-dimensional turbulent boundary layer at a nominal free-stream Mach number of 2 and unit Reynolds number of 8 million per meter. The displacement obtained in the study was larger than that reported by previous investigators in either an incompressible turbulent boundary layer or a supersonic laminar boundary layer. The large probes indicated distorted Mach number profiles, probably due to separation. When the probes were small enough to cause no appreciable distortion, the displacement was constant over most of the boundary layer. The displacement in the near-wall region decreased to negative displacement in some cases. This near-wall region was found to extend to about one probe diameter from the test surface.
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:
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:
Download or read book NASA Technical Note written by and published by . This book was released on 1973 with total page 736 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Flight measured Pressure Characteristics of Aft facing Steps in High Reynolds Number Flow at Mach Numbers of 2 20 2 50 and 2 80 and Comparison with Other Data written by Sheryll Goecke Powers and published by . This book was released on 1978 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1969 with total page 1090 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book In flight Use of Traversing Boundary layer Probes written by Edwin J. Saltzman and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two prototype traversing boundary-layer pitot probes were demonstrated in flight. A motor-operated screw-driven type of probe was used on two jet aircraft for defining boundary layers at profile edge Mach numbers from 0.5 to 2.2. The other type of traversing probe was motor driven through a Scotch yoke mechanism and was operated on several flights of the X-15 airplane. The highest free-stream Mach number reached during this series of flights was 5. 6. The mechanical and electrical features of these probes are described, and photographs and conceptual drawings are included. Problems encountered during the development of the devices are described, and the solutions that were found are explained. Boundary-layer profile data are presented in several forms, and local friction coefficients derived from the profile through a Clauser type of determination are shown.
Download or read book Experimental Results for a Hypersonic Nozzle afterbody Flow Field written by Frank W. Spaid and published by . This book was released on 1995 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Summary and Correlation of Skin friction and Heat transfer Data for a Hypersonic Turbulent Boundary Layer on Simple Shapes written by Edward J. Hopkins and published by . This book was released on 1969 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Skin friction and heat transfer data for hypersonic turbulent layer on flat plates, wind tunnel wall, and cones.
