Download or read book An Experimental Investigation of Hypersonic Viscous Interaction on a Sharp Leading Edge Flat Plate written by Jeffrey Whipple and published by . This book was released on 1973 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Investigation of a Flat plate in Hypersonic Flow with Viscous and Bluntness Interactions written by Harold Eugene Deskins and published by . This book was released on 1964 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Model for the Sharp Leading Edge Problem in Rarefied Hypersonic Flow written by W. J. McCroskey and published by . This book was released on 1966 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flow field studies of the shock wave and boundary layer development on a sharp flat plate are presented for a region of rarefied flow that bridges the gap between a classical hypersonic boundary layer downstream and a kinetic flow model at the leading edge. The measurements give a comprehensive picture of the flow pattern in the 'merged layer' or 'viscous layer' regime, which exists upstream of the region of validity of hypersonic viscous interaction theory. The results are derived from a combination of several probing and optical techniques and surface pressure measurements. From the detailed measurements, a true scale physical model of the flow field is constructed for the merged layer regime. One of the main features of the model is a thick, curved shock wave which decreases in strength as the leading edge is approached, even though the shock angle increases. Density profiles across the shock and viscous layers show that the structure of the flow field is quite different from the classical picture of a hypersonic boundary layer beneath an oblique Rankine-Hugonio shock wave. (Author).

Download or read book Hypersonic Viscous Interaction An Experimental Investigation of the Flow Over Flat Plates at Incidence and Around an Expansion Corner written by John L. Stollery and published by . This book was released on 1970 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flat plate and expansion corner models were tested over a range of positive and negative incidences in a continuous hypersonic wind tunnel operating at M = 14.8. Surface pressure distributions were obtained for comparison with the viscous interaction theories of Cheng and Sullivan. Since these theories assume 'local flat plate similarity' for the boundary layer flow, pitot pressure profiles were measured at various stations along the plates. It often proved difficult to define the boundary layer edge within the shock layer and total temperature profiles would greatly assist in interpreting the data. Schlieren pictures and oil flow visualization gave good indications of the extent of end effects, the onset of separation caused by the trailing edge shock wave, and tunnel blocking at high model incidence. The tests have provided some new hypersonic experimental data under conditions where both strong viscous interaction and incidence effects are important. (Author).

Download or read book On Hypersonic Viscous Flow Near a Sharp Leading Edge written by Richard W. Garvine and published by . This book was released on 1966 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical inquiry is made into the high speed viscous flow past a sharp-edged flat plate whose surface is aligned with the oncoming flow. Basic information is sought concerning the fundamental nature of the flow field in regions near the leading edge. The role of upstream conditions is found to be fundamental. Study is made of the viscous layer region on the two-dimensional flat plate ahead of the strong interaction region. The Navier-Stokes equations are applied to the flow up to the point where continum treatments are no longer justifiable. Two initial velocity profiles were assumed in order to examine the details of the theory. Neither form proved to yield realistic flow fields in the light of experimental results. Computations from these two profile forms, however, did serve to bring out the sensitivity of the flow throughout the viscous layer region to initial conditions. It is concluded, in consequence, that the flow cannot be described by similar solutions or other solutions which ignore these initial values. (Author).

Download or read book NASA Technical Note written by and published by . This book was released on 1971 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Critical Assessment of the Problem of Sharp Leading Edge of a Flat Plate in Hypersonic Flow written by Amolak C. Jain and published by . This book was released on 1964 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The advent of vehicles, moving many times the velocity of sound makes it necessary to understand clearly the various phenomena occuring near the sharp leading edge of a flat plate. A few theoretical attempts to tackle this problem are made and several experiments are performed at various places. Unfortunately wide areas of disagree ment exist between the various theoretical investigations and experimental results. It is the purpose of the note to try to gather some useful information from the available literature on this subject and present some suggestions which might be useful or worth consideration in any future attempt of solving this problem. (Author).

Download or read book Viscous Interactions at Hypersonic Speed written by Michael S. Holden and published by . This book was released on 1986 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been directed toward investigations of fundamental aerothermal phenomena in hypersonic flow, with particular emphasis on viscous/inviscid interaction phenomena. The experimental studies were conducted to examine the changes in the structure at the base of a hypersonic turbulent boundary layer as it is subjected to a strong self induced pressure gradient in regions of shock wave/boundary layer interaction. The initial phase of the theoretical program was directed toward summarizing existing techniques for obtaining Navier/Stokes solutions for laminar flow over flat plates in hypersonic flow. In the experimental program, surface and flow field measurements were made to examine the detailed flow mechanics associated with turbulent boundary layer separation over a large cone flare model at Mach 11, 13, and 16 for Reynold numbers up to 100 million. Solutions have been obtained to Navier-Stokes equations for the laminar flow over the leading edge of a sharp flat plate in Mach 16 flow for highly cooled wall conditions using a modified MacCormack/Shang fully explicit formulation. To obtain a stable converged solution it was necessary to reduce the grid size close to the leading edge to the order of the mean free path, and typically 20,000 time steps were required to achieve convergence. However, once obtained, the solution was a good agreement with experiment.

Download or read book Effect of Slight Blunting of Leading Edge of an Immersed Body on the Flow Around it at Hypersonic Speeds written by Goromir Goromirovich Chernyĭ and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Masters Theses in the Pure and Applied Sciences written by Wade H. Shafer and published by Springer Science & Business Media. This book was released on 2013-12-11 with total page 299 pages. Available in PDF, EPUB and Kindle. Book excerpt: Masters Theses in the Pure and Applied Sciences was first conceived, published, and dis seminated by the Center for Information and Numerical Data Analysis and Synthesis, (CINDAS) *at Purdue University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dissemination phases of the ac tivity was transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all concerned if the printing and distribution of the volume were handled by an international publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Corporation of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 19 (thesis year 1974) a total of 10,045 theses titles from 20 Canadian and 209 United States universities. We are sure that this broader base for theses titles reported will greatly enhance the value of this important annual reference work. The organization of Volume 19 is identical to that of past years. It consists of theses titles arranged by discipline and by university within each discipline.

Download or read book An Experimental Investigation of Leading Edge Shock Wave boundary Layer Interaction at Hypersonic Speeds written by James Madison Kendall and published by . This book was released on 1956 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Leading edge Bluntness on Pressure and Heat transfer Measurements Over a Flat Plate at a Mach Number of 20 written by William D. Harvey and published by . This book was released on 1965 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Viscous Hypersonic Flow written by William H. Dorrance and published by Courier Dover Publications. This book was released on 2017-05-22 with total page 353 pages. Available in PDF, EPUB and Kindle. Book excerpt: Designed for advanced undergraduate and graduate courses in modern boundary-layer theory, this frequently cited work offers a self-contained treatment of theories for treating laminar and turbulent boundary layers of reacting gas mixtures. 1962 edition.

Download or read book A Flat Plate Study of the Binary Scaling of Viscous Hypersonic Flow written by D. J. Harney and published by . This book was released on 1971 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: The interaction between the inviscid field and the large viscous boundary layer characteristic of hypersonic flow is analyzed from the continuum viewpoint. A variety of similarity parameters are derived to represent the viscous flow over slender bodies. The similitude is described by a binary collision scaling parameter, so that it is possible to apply a binary scaling that transforms density and length in inverse proportion at a fixed velocity and temperature. Experiments at a Mach number near 13 on a thermally controlled copper sharp plate were conducted to examine the wall temperature effects. Because of the wide range of test conditions covered in the experiments, the results provide some insight into viscous similarity when molecular effects begin to appear at the leading edge.

Download or read book Experimental Investigation of Leading Edge Shock Wave boundary Layer Interaction at Hypersonic Speeds written by James M. Kendall and published by . This book was released on 1956 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical Analysis of Near free molecule Hypersonic Flow at the Sharp Leading Edge of a Flat Plate written by A. F. Charwat and published by . This book was released on 1963 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: The initial interactions between a hypersonic free stream and molecules emitted (reflected diffusely) by a cold flat plate immediately downstream of its sharp leading edge are analyzed by near-free-molecule theory. The results give the variations of the pressure, shear, and heat transfer at the wall. These are found to in crease downstream from the leading edge and reach a maximum plateau, and a subsequent decay of the wall-transfer properties to continuum boundary-layer values can be inferred. The magnitude and location of this plateau compare well with available viscous pressure interaction data. An indication of the initial growth rate of the disturbed merged layer is also obtained from the analysis. It is found that this region is wedgelike and has a slope of approximately 45 deg for all hypersonic Mach numbers and for wall to- free-stream-temperature ratios of the order of unit.

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1974 with total page 592 pages. Available in PDF, EPUB and Kindle. Book excerpt: