Hypersonic Inviscid Flow Along a Corner Consisting of Two Wedges with Sharp Leading Edges
Author | : Robert McLaughlin Wright (Jr.) |
Publisher | : |
Total Pages | : 88 |
Release | : 1965 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
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Author | : Robert McLaughlin Wright (Jr.) |
Publisher | : |
Total Pages | : 88 |
Release | : 1965 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Author | : Wallace D. Hayes |
Publisher | : Courier Corporation |
Total Pages | : 628 |
Release | : 2012-07-13 |
Genre | : Science |
ISBN | : 0486160483 |
Unified, self-contained view of nonequilibrium effects, body geometries, and similitudes available in hypersonic flow and thin shock layer; appropriate for graduate-level courses in hypersonic flow theory. 1966 edition.
Author | : Robert J. Cresci |
Publisher | : |
Total Pages | : 36 |
Release | : 1966 |
Genre | : |
ISBN | : |
The present paper deals with an experimental study of the viscous-inviscid interaction occuring in a corner region under hypersonic, low density, free stream conditions. The tests were conducted in the Mach 11.8 hypersonic tunnel at PIBAL over a range of free stream Reynolds numbers between 0.15 x 10 to the 6th and 0.50 x 10 to the 6th/ft. The model consists of two sharp edged plates mounted at an angle of 90 degrees with respect to each other and with normal leading edges. Data obtained include surface measurements of pressure and heat transfer for values of the interaction parameter between 1.0 and 20. The entire corner region is surveyed at a value of 2.5 and measurements of total temperature, pitot, and static pressure are obtained. The results indicate that the static pressure in the region of intersection of the shock layers is as much as twice that of the local two dimensional value. The local heat rates in this region are also considerably larger than their two dimensional counterparts. (Author).
Author | : Hakuro Oguchi |
Publisher | : |
Total Pages | : 86 |
Release | : 1960 |
Genre | : Leading edges (Aerodynamics) |
ISBN | : |
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 | : Joseph J.S. Shang |
Publisher | : CRC Press |
Total Pages | : 327 |
Release | : 2023-04-28 |
Genre | : Science |
ISBN | : 1000876993 |
Classic and High-Enthalpy Hypersonic Flows presents a complete look at high-enthalpy hypersonic flow from a review of classic theories to a discussion of future advances centering around the Born-Oppenheim approximation, potential energy surface, and critical point for transition. The state-of-the-art hypersonic flows are defined by a seamless integration of the classic gas dynamic kinetics with nonequilibrium chemical kinetics, quantum transitions, and radiative heat transfer. The book is intended for graduate students studying advanced aerodynamics and taking courses in hypersonic flow. It can also serve as a professional reference for practicing aerospace and mechanical engineers of high-speed aerospace vehicles and propulsion system research, design, and evaluation. Features Presents a comprehensive review of classic hypersonic flow from the Newtonian theory to blast wave analogue. Introduces nonequilibrium chemical kinetics to gas dynamics for hypersonic flows in the high-enthalpy state. Integrates quantum mechanics to high-enthalpy hypersonic flows including dissociation and ionization. Covers the complete heat transfer process with radiative energy transfer for thermal protection of earth reentry vehicle. Develops and verifies the interdisciplinary governing equations for understanding and analyzing realistic hypersonic flows.
Author | : Michael Lewis Shorenstein |
Publisher | : |
Total Pages | : 31 |
Release | : 1971 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
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 | : Wallace Dean Hayes |
Publisher | : |
Total Pages | : 632 |
Release | : 1966 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |