The Problem Of Sharp Leading Edge In Hypersonic Flow
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| Author | : Amolak C. Jain |
| Publisher | : |
| Total Pages | : 51 |
| Release | : 1963 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download The Problem of Sharp Leading Edge in Hypersonic Flow Book in PDF, Epub and Kindle
In what follows an attempt is made to present the analysis of this problem without the restric tion of wedge-like flow model and at the same time remove certain discrepancies in Oguchi's work. A new transformation is found and a series solution of the resulting equation is evolved. Analytical expressions for the first two terms of this series are obtained. The induced pressures computed on the basis of these two terms is com pared with the experimental results of Nagamatsu, Sheer and Weil. We find that, in the range of validity of our solution, the theoretical predic tion of the induced pressure agrees fairly well within a certain Mach Number range with the experimental data of Nagamatsu, Sheer and Weil.
| Author | : Hakurō Oguchi |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1960 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download The Sharp Leading Edge Problem in Hypersonic Flow Book in PDF, Epub and Kindle
| Author | : Hakuro Oguchi |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1960 |
| Genre | : Leading edges (Aerodynamics) |
| ISBN | : |
Download The Sharp Leading Edge Problem in Hypersonic Flow Book in PDF, Epub and Kindle
In the present paper the problem of hypersonic viscous flow past a semi-infinite flat plate with a sharp leading edge is considered. The study is concerned primarily with the rarefied flow region close enough to the leading edge that there is no longer an inviscid layer but where the shock wave is still thin. The solution which is obtained is shown to approach a wedge-like flow near the leading edge with a straight induced shock wave.
| Author | : Amolak C. Jain |
| Publisher | : |
| Total Pages | : 42 |
| Release | : 1964 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download A Critical Assessment of the Problem of Sharp Leading Edge of a Flat Plate in Hypersonic Flow Book in PDF, Epub and Kindle
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).
| Author | : W. J. McCroskey |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1966 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download An Experimental Model for the Sharp Leading Edge Problem in Rarefied Hypersonic Flow Book in PDF, Epub and Kindle
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).
| Author | : Jay M. Solomon |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1965 |
| Genre | : |
| ISBN | : |
Download On the Hypersonic Sharp Leading Edge Problem for Bodies Other Than Flat Plates Book in PDF, Epub and Kindle
The flow near the tip of pointed nosed bodies in hypersonic flight is considered. In particular, the region where continuum concepts are applicable, but where boundary layer theory is no longer valid, is studied using the model proposed by Oguchi for the flat plate problem. Both two-dimensional and axiallysymmetric bodies are considered. Solutions are obtained in the form of expansions valid near the nose tip. The surface pressure is found to approach a finite value as the tip is approached; numerical results for this limit value are obtained for various wall to total temperature ratios and tip semi-vertex angles. (Author).
| Author | : James Courtland Townsend |
| Publisher | : |
| Total Pages | : 34 |
| Release | : 1966 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download Effects of Leading-edge Bluntness and Ramp Deflection Angle on Laminar Boundary-layer Separation in Hypersonic Flow Book in PDF, Epub and Kindle
| Author | : Michael Lewis Shorenstein |
| Publisher | : |
| Total Pages | : 31 |
| Release | : 1971 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download The Hypersonic Leading Edge Problem. II. Wedges and Cones Book in PDF, Epub and Kindle
An analysis is given for the viscous hypersonic flow past slender sharp wedges and unyawed cones. The leading edge or nose region treated encompasses the merged layer regime in which the shock thickness is not small in comparison with the viscous layer thickness but for which in the axisymmetric case the shock thickness is small in comparison with the radius of transverse shock curvature. A Navier-Stokes flow is assumed, and both the shock structure and viscous layer are taken to be locally-similar of boundary layer type. The analysis follows that used by Shorenstein and Probstein for the corresponding flat plat problem. For axisymmetric cone flow, a modification of a transformation introduced by Probstein and Elliott is given to reduce the axisymmetric viscous layer equations including transverse curvature to 'exactly' two-dimensional form. Results for the state conditions behind the shock, and the wall pressure, skin friction, and heat transfer rate are found to be in agreement with available experimental data.
| Author | : G. M. Poedintsev |
| Publisher | : |
| Total Pages | : 16 |
| Release | : 1969 |
| Genre | : |
| ISBN | : |
Download Hypersonic Gas Flow Past a Flat Plate with a Sharp Leading Edge Book in PDF, Epub and Kindle
The problem of hypersonic gas flow over a plane plate with a sharp leading edge is discussed. It is assumed that the gas is perfect with a constant specific heat ratio and that the plate is thermally insulated. The problem is solved theoretically on the basis of a model which makes use of the geometrical characteristics of the Navier-Stokes equations. (Author).
| Author | : Richard W. Garvine |
| Publisher | : |
| Total Pages | : 48 |
| Release | : 1968 |
| Genre | : |
| ISBN | : |
Download A Study of the Hypersonic Leading Edge Flow in the Merged Layer and Strong Interaction Regimes Book in PDF, Epub and Kindle
The problem of hypersonic flow near the leading edge of a sharp-edged body is investigated. The region of chief interest is the merged layer flow regime just upstream of the strong interaction regime. The limitations of applying continuum equations to the leading edge flow are discussed. A system of composite equations applicable to the merged layer and strong interaction flow regime is then developed systematically from the Navier-Stokes equations for the steady, planar or axi-symmetric flow of a perfect gas. Limited numerical solutions of these equations are described for the case of a sharp-edged flat plate. Owing to the presence of weak upstream influence in the problem, divergent behavior is encountered in the numerical treatment of the problem. The divergence scale is quite small, and prevents extensive calculations for the merged layer from being made. It is concluded that another means for numerical solution of the equations is required if practical computation times are to be achieved. (Author).
