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Author: Robert J. Cresci Publisher: ISBN: Category : Languages : en Pages : 65
Book Description
A study has been made of transpiration cooling of typical hypersonic re-entry configurations with a primary emphasis on experimental data acquisition, although some limited analytical and numerical support studies have been undertaken. The experiments have been conducted in the hypersonic flow region, under zero and non-zero angle of attack conditions, and covering the range in Reynolds numbers required to obtain laminar, transitional, and turbulent data. Numerical and analytical studies have been performed of viscous and interacting viscous-inviscid flows with application to 3D boundary layers, wing-body configurations, and internal flow problems. In this area, the development of numerical techniques and analytical tools is of primary significance although the application of these methods to practical problems of interest has also been accomplished. (Author).
Author: Robert J. Cresci Publisher: ISBN: Category : Languages : en Pages : 65
Book Description
A study has been made of transpiration cooling of typical hypersonic re-entry configurations with a primary emphasis on experimental data acquisition, although some limited analytical and numerical support studies have been undertaken. The experiments have been conducted in the hypersonic flow region, under zero and non-zero angle of attack conditions, and covering the range in Reynolds numbers required to obtain laminar, transitional, and turbulent data. Numerical and analytical studies have been performed of viscous and interacting viscous-inviscid flows with application to 3D boundary layers, wing-body configurations, and internal flow problems. In this area, the development of numerical techniques and analytical tools is of primary significance although the application of these methods to practical problems of interest has also been accomplished. (Author).
Author: M. H. Bloom Publisher: ISBN: Category : Languages : en Pages : 54
Book Description
The paper presents results of analysis and experiment bearing on three-dimensional effects in hypersonic interaction, with emphasis on a sharp-edged rectangular corner intersection aligned with the flow and a sharp-edged plate of finite span. A powerful tool for dealing with such complex problems is the 'merged-layer approximation' which obviates the need for complicated matching procedures in many instances of importance although numerical computation is required. This type of flow, in which various elements are strongly coupled and even merged, is shown to have features in common with low-speed three-dimensional boundary layers such as those along an interior corner or along the edge of a quarter-infinite plate. In the low speed cases the essential viscous-inviscid interaction coupling enters through the weak, Reynolds-number dependent, displacements of the inviscid flow which must be taken into account even to lowest order. The attendant analytics and numerics are in many respects more difficult to deal with than those of the hypersonic counterparts. (Author).
Author: AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO. Publisher: ISBN: Category : Languages : en Pages : 566
Book Description
The symposium focused on departures from the classical boundary layer theories toward shock wave-boundary layer interactions with their attendant flow separation and reattachment and toward the three-dimensional viscous interactions of practical configurations. It thus dealt with one of the key problem areas associated with high speed supersonic aircraft, lifting-reentry vehicles, and potential hypersonic cruise vehicles. Such configurations are highly three-dimensional with complex flows involving strong viscous-inviscid interactions in regions of compression such as in air breathing engine inlets, at wing-body junctions, and over control surfaces. (Author).
Author: Ernst Heinrich Hirschel Publisher: Springer Science & Business Media ISBN: 3642413781 Category : Technology & Engineering Languages : en Pages : 396
Book Description
Viscous flow is treated usually in the frame of boundary-layer theory and as two-dimensional flow. Books on boundary layers give at most the describing equations for three-dimensional boundary layers, and solutions often only for some special cases. This book provides basic principles and theoretical foundations regarding three-dimensional attached viscous flow. Emphasis is put on general three-dimensional attached viscous flows and not on three-dimensional boundary layers. This wider scope is necessary in view of the theoretical and practical problems to be mastered in practice. The topics are weak, strong, and global interaction, the locality principle, properties of three-dimensional viscous flow, thermal surface effects, characteristic properties, wall compatibility conditions, connections between inviscid and viscous flow, flow topology, quasi-one- and two-dimensional flows, laminar-turbulent transition and turbulence. Though the primary flight speed range is that of civil air transport vehicles, flows past other flying vehicles up to hypersonic speeds are also considered. Emphasis is put on general three-dimensional attached viscous flows and not on three-dimensional boundary layers, as this wider scope is necessary in view of the theoretical and practical problems that have to be overcome in practice. The specific topics covered include weak, strong, and global interaction; the locality principle; properties of three-dimensional viscous flows; thermal surface effects; characteristic properties; wall compatibility conditions; connections between inviscid and viscous flows; flow topology; quasi-one- and two-dimensional flows; laminar-turbulent transition; and turbulence. Detailed discussions of examples illustrate these topics and the relevant phenomena encountered in three-dimensional viscous flows. The full governing equations, reference-temperature relations for qualitative considerations and estimations of flow properties, and coordinates for fuselages and wings are also provided. Sample problems with solutions allow readers to test their understanding.
Author: John Webster Ellinwood Publisher: ISBN: Category : Aerodynamics, Hypersonic Languages : en Pages : 50
Book Description
Stewartson's theory for axisymmetric hypersonic flow of a model gas with strong viscous interaction and strong shock wave is extended to power-law viscosity variation, nonunit Prandtl number, and body shapes other than power laws. For power-law bodies, the generalized theory is obtained in closed form without recourse to numerical integration. In addition, numerical computations are presented for axisymmetric flow over a three-quarter power-law body with strong shock wave and viscous interactions that range from weak to strong. (Author).
Author: Robert J. Cresci Publisher: ISBN: Category : Languages : en Pages : 25
Book Description
Surface heat transfer and boundary layer transition measurements have been performed on a slender blunted cone at M(infinity) = 8.0. These measurements have been obtained on the conical surface with mass transfer occurring on the spherical nose cap. The free stream Reynolds number, based on nose radius, varied between 6000 and 90000. Data was obtained both at zero angle of attack and at angles as high as 14 deg, which exceeds the semi-vortex cone angle of 10 deg. The technique utilized in the determination of transition location was a thin film gauge, on the model surface, which was maintained at a constant temperature by an anemometer system. The RMS output of the film gauge was found to accurately locate the onset of boundary layer transition. A numerical analysis of film cooling in the stagnation region of a slender cone was also performed using the thin shock layer approximation. The porous region was analyzed and compared to previously obtained results using different assumptions. The downstream region, at angle of attack, utilize the porous region results as initial conditions. The computer program, however, was not successfully operated in this mode.
Author: Datta V. Gaitonde Publisher: ISBN: Category : Aerodynamics, Hypersonic Languages : en Pages : 64
Book Description
The interaction of an impinging shock with the bow-shock generated by a blunt geometry is examined numerically for hypersonic (Mach 8, perfect gas) flows with modified Steger-Warming flux-split scheme. The modifications are designed to reduce numerical dissipation in the boundary layer thus improving the resolution and accuracy of the resulting algorithm. The full 2-D Navier- Stokes equations are solved in finite-volume formulation with central differencing for viscous terms and residual driven line Gauss-Seidel relaxation for time advancement. Grid resolution studies are performed. For a Type IV interaction, comparison with surface pressure and heat-transfer rates display good overall agreement with experimental values. For a Type III+ interaction, a detailed comparison is made with experimental surface quantities and a computation with Van Leer's flux-splitting algorithm. The peak amplification of pressure is modestly overpredicted with the current algorithm. The computed peak heat transfer is comparable to that obtained in previous research with Van Leer's splitting, although anomalous behavior is observed in the vicinity of the stagnation point. This behavior may be eliminated with appropriate corrections.
Author: Robert J. Cresci
Author: Robert J. Cresci
Author: Francis X. Hurley
Author: M. H. Bloom
Author: AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO.
Author: 
Author: Ernst Heinrich Hirschel
Author: John Webster Ellinwood
Author: Robert J. Cresci
Author: Datta V. Gaitonde
Author: Tony C. Lin