Two-Dimensional Turbulent Boundary Layer Separation on a Flat Plate with Ramp at Freestream Mach Numbers of 3.7 and 6.3 in Supersonic and Hypersonic Flow PDF Download
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Author: Victor Zakkay Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 52
Book Description
This investigation describes surface pressure distribution, heat transfer, and turbulent flow separation and reattachment on a flat plate with variable ramp angle at Mach numbers averaging 3.66 and 6.30. The freestream Reynold's number varied from 3.33 to 8.34 million per foot for the former case and from 5.243 million to 14.6 million per foot for the latter case. Ramp angle was varied from 0 to 35 degrees for these experiments. Stagnation temperatures averaged 849 degrees Rankine, with wall temperature assumed constant at 535 degrees Rankine for all tests. The knowledge of effective wedge angles and freestream conditions makes it possible to determine shocks so that conditions can be evaluated at all positions on the model.
Author: Victor Zakkay Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 52
Book Description
This investigation describes surface pressure distribution, heat transfer, and turbulent flow separation and reattachment on a flat plate with variable ramp angle at Mach numbers averaging 3.66 and 6.30. The freestream Reynold's number varied from 3.33 to 8.34 million per foot for the former case and from 5.243 million to 14.6 million per foot for the latter case. Ramp angle was varied from 0 to 35 degrees for these experiments. Stagnation temperatures averaged 849 degrees Rankine, with wall temperature assumed constant at 535 degrees Rankine for all tests. The knowledge of effective wedge angles and freestream conditions makes it possible to determine shocks so that conditions can be evaluated at all positions on the model.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
An experimental investigation of laminar boundary-layer separation induced by a trailing edge ramp on a flat plate was conducted at Mach numbers of 6, 8, and 10. The tests were conducted over a range of Reynolds numbers. Longitudinal and spanwise surface pressure distributions, pitot pressure profiles, and shadowgraph pictures were used to investigate the two-dimensionality of the flow and the effects of model geometry, angle of attack, Reynolds number, ramp angle, and mass removal from the separation region. Data are presented to show that laminar, two-dimensional boundary-layer reattachment, not limited by model geometry, was obtained. These data are compared to the integral-moment theory of Lees and Reeves as modified by Klineberg. It is also shown that a separation region can be reduced or even eliminated by removing mass at the hinge line. (Author).
Author: Arnold Polak Publisher: ISBN: Category : Boundary layer control Languages : en Pages : 58
Book Description
The report presents an analysis predicting separation of a turbulent boundary layer over a cone-flare configuration with gas injected into the boundary layer ahead of separation point. Separation location and separation lengths are compared with experimental data obtained at Mach number of 6 and a range of Reynolds numbers. At the highest Reynolds numbers the extent of separation decreases with increasing Reynolds number. When compared to separation over cylinder-flare body it is found that the extent of separation is lower for the cone-flare configuration. (Author).
Author: Anthony W. Fiore Publisher: ISBN: Category : Turbulent boundary layer Languages : en Pages : 962
Book Description
In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.
Author: Holger Babinsky Publisher: Cambridge University Press ISBN: 1139498649 Category : Technology & Engineering Languages : en Pages : 481
Book Description
Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Author: Victor Zakkay
Author: Victor Zakkay
Author: Robert Allan White
Author: Von Karman Institute for Fluid Dynamics
Author: 
Author: C. Appels
Author: Arnold Polak
Author: Donald M. Kuehn
Author: Anthony W. Fiore
Author: 
Author: Holger Babinsky