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Flight Measured Base Pressure Coefficients For Thick Boundary Layer Flow Over An Aft Facing Step For Mach Numbers From 04 To 25
Download Flight Measured Base Pressure Coefficients For Thick Boundary Layer Flow Over An Aft Facing Step For Mach Numbers From 04 To 25 full books in PDF, epub, and Kindle. Read online Flight Measured Base Pressure Coefficients For Thick Boundary Layer Flow Over An Aft Facing Step For Mach Numbers From 04 To 25 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Flight-measured Base Pressure Coefficients for Thick Boundary-layer Flow Over an AFT-facing Step for Mach Numbers from 0.4 to 2.5/ by Sheryll A. Goecke by : Sheryll A. Goecke
Download or read book Flight-measured Base Pressure Coefficients for Thick Boundary-layer Flow Over an AFT-facing Step for Mach Numbers from 0.4 to 2.5/ by Sheryll A. Goecke written by Sheryll A. Goecke and published by . This book was released on 1973 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight-measured Base Pressure Coefficients for Thick Boundary-layer Flow Over an Aft-facing Step for Mach Numbers from 0.4 to 2.5 by : Sheryll A. Goecke
Download or read book Flight-measured Base Pressure Coefficients for Thick Boundary-layer Flow Over an Aft-facing Step for Mach Numbers from 0.4 to 2.5 written by Sheryll A. Goecke and published by . This book was released on 1973 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Sheryll Goecke Powers
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 46 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 1973 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781726013260 Total Pages :38 pages Book Rating :4.0/5 (132 download)
Book Synopsis 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 by : National Aeronautics and Space Administration (NASA)
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 National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-22 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: The YF-12 airplane was studied to determine the pressure characteristics associated with an aft-facing step in high Reynolds number flow for nominal Mach numbers of 2.20, 2.50, and 2.80. Base pressure coefficients were obtained for three step heights. The surface static pressures ahead of and behind the step were measured for the no-step condition and for each of the step heights. A boundary layer rake was used to determine the local boundary layer conditions. The Reynolds number based on the length of flow ahead of the step was approximately 10 to the 8th power and the ratios of momentum thickness to step height ranged from 0.2 to 1.0. Base pressure coefficients were compared with other available data at similar Mach numbers and at ratios of momentum thickness to step height near 1.0. In addition, the data were compared with base pressure coefficients calculated by a semiempirical prediction method. The base pressure ratios are shown to be a function of Reynolds number based on momentum thickness. Profiles of the surface pressures ahead of and behind the step and the local boundary layer conditions are also presented. Powers, S. G. Armstrong Flight Research Center NASA-TM-72855, H-956 RTOP 505-06-34...
Book Synopsis Base Pressure Coefficients Obtained from the X-15 Airplane for Mach Numbers Up to 6 by : Edwin J. Saltzman
Download or read book Base Pressure Coefficients Obtained from the X-15 Airplane for Mach Numbers Up to 6 written by Edwin J. Saltzman and published by . This book was released on 1964 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Publisher : ISBN 13 : Total Pages :1232 pages Book Rating :4.:/5 (31 download)
Book Synopsis AGARD Conference Proceedings by : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Download or read book AGARD Conference Proceedings written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development and published by . This book was released on 1973 with total page 1232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Thickness on the Flow Over a Flat Plate at a Mach Number of 5.7 by : Marcus O. Creager
Download or read book Effect of Leading-edge Thickness on the Flow Over a Flat Plate at a Mach Number of 5.7 written by Marcus O. Creager and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Simplified Method for Determination of Critical Height of Distributed Roughness for Boundary-layer Transition at Mach Numbers from 0 to 5 by : Albert L. Braslow
Download or read book Simplified Method for Determination of Critical Height of Distributed Roughness for Boundary-layer Transition at Mach Numbers from 0 to 5 written by Albert L. Braslow and published by . This book was released on 1958 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt: The method has been applied to various types of configurations in several wind-tunnel investigations conducted by the National Advisory Committee for Aeronautics at Mach numbers up to 4, and in all cases the calculated roughness height caused premature boundary-layer transition for the range of test conditions.
Book Synopsis The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers by : Roger L. Kimmel
Download or read book The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers written by Roger L. Kimmel and published by . This book was released on 1993 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7 degrees half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.
Book Synopsis Pressures Measured in Flight on the Aft Fuselage and External Nozzle of a Twin-jet Fighter by :
Download or read book Pressures Measured in Flight on the Aft Fuselage and External Nozzle of a Twin-jet Fighter written by and published by . This book was released on 1983 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparison of Wind-tunnel and Flight-measured Base Pressures from the Sharp-leading-edge Upper Vertical Fin of the X-15 Airplane for Turbulent Flow at Mach Numbers from 1.5 to 5.0 by : Sheryll Goecke Powers
Download or read book Comparison of Wind-tunnel and Flight-measured Base Pressures from the Sharp-leading-edge Upper Vertical Fin of the X-15 Airplane for Turbulent Flow at Mach Numbers from 1.5 to 5.0 written by Sheryll Goecke Powers and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Index written by and published by . This book was released on 1973 with total page 1068 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing by : John A. Zalovcik
Download or read book Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing written by John A. Zalovcik and published by . This book was released on 1944 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.
Book Synopsis Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 by : Mitchel H. Bertram
Download or read book Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 written by Mitchel H. Bertram and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer by : Robert L. P. Voisinet
Download or read book Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer written by Robert L. P. Voisinet and published by . This book was released on 1972 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a zero-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall for a nominal Mach number of 4.9, at momentum thickness Reynolds numbers from 7,000. to 58,000. and at wall-to-adiabatic-wall temperature ratios of 1.0, 0.8 and 0.25. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. Furthermore, the wall shear and surface heat transfer were measured directly with a skin-friction balance and a heat-transfer gage, respectively. (Author Modified Abstract).
Book Synopsis A Method of Calculating Turbulent-boundary-layer Growth at Hypersonic Mach Numbers by : James C. Sivells
Download or read book A Method of Calculating Turbulent-boundary-layer Growth at Hypersonic Mach Numbers written by James C. Sivells and published by . This book was released on 1959 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed for calculating the growth of a turbulent boundary layer at hypersonic Mach numbers. Excellent agreement with experimental results from axisymmetric nozzles has been obtained by the application of this method. The method utilizes a modification of Stewartson's transformation to simplify the integration of the momentum equation. Heat transfer is taken into account by evaluating the gas properties at Eckert's reference temperature and by using a modification of Crocco's quadratic for the temperature distribution in the boundary layer. A new empirical relation is used for the incompressible friction coefficient which agrees with experimental data over a Reynold's number range from 10(superscript 5) to 10(superscript 9).
