3 edition of Wall pressure fluctuations in the reattachment region of a supersonic free shear layer found in the catalog.
Wall pressure fluctuations in the reattachment region of a supersonic free shear layer
Alexander J. Smits
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va
Written in English
|Statement||by Alexander J. Smits.|
|Series||[NASA contractor report] -- NASA CR-195790., NASA contractor report -- NASA CR-195790.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
) A supersonic stream at 1 M = flows past a compression corner with a deflection angle of The incident shock wave is reflected from an opposite wall which is parallel to the upstream supersonic flow, as sketched in Fig. Calculate the angle of the reflected shock relative to the straight wall. The boundary layer consisted of 24 layers with the closest point to the wall located at a distance of approximately y + ≈ in wall units. A close-up of the boundary layer elements can be observed in Figure 1b. A region with a bottom symmetry condition was imposed upstream of Cited by: 3.
Intro The initial idea that led to the creation of ReConAn v Finite Element Analysis Program was to provide an Analysis Tool for Reinforced Concrete Structures, a . Procedure for Calculating the development of Turbulent Boundary Layers under the Influence of adverse pressure Gradients (NACA TN ) [Kennedy F. Rubert] on *FREE* shipping on qualifying offers. Procedure for Calculating the development of Turbulent Boundary Layers under the Influence of adverse pressure Gradients (NACA TN ).
Abstract. A method for the theoretical determination of the wall shear stress under impinging jets of various congurations is presented. Axisymmetric and two-dimensional incompres. 37th AIAA Fluid Dynamics Conference and Exhibit. 25 June - 28 June Miami, Florida. Separated Shear Layer Transition at Low Reynolds Numbers: Experiments and Stability Analysis Wall-Effects on Pressure Fluctuations in Quasi-Incompressible and Compressible Turbulent Plane .
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Wall Pressure Fluctuations in the Reattachment Region of a Supersonic Free Shear Layer by Professor Alexander J. Smits Department of Mechanical and Aerospace Engineering Princeton University Princeton, NJ Attention: Dr. William E. Zorumski Chief Scientist Fluid Mechanics and Acoustics Division Mail Stop NASA Langley Research Center.
A study was made of the wall pressure fluctuations in the reattachment region of a supersonic free shear layer. The free shear layer was formed by the separation of a Mach turbulent boundary layer from a backward facing step.
Reattachment occurred on a 20° ramp. By adjusting the position of the ramp, the base pressure at the step was set equal to the freestream pressure, and the Cited by: Get this from a library. Wall pressure fluctuations in the reattachment region of a supersonic free shear layer.
[Alexander J Smits; United States. National Aeronautics and Space Administration.]. Wall pressure fluctuations were measured in the reattachment region of the supersonic free shear layer.
The free shear layer was formed by the separation of a Mach turbulent boundary layer. Then, the primary structural flow elements can be identified: the reattachment shock C 3, the high total pressure layer DL located above the boundary layer corresponding to the dark horizontal band in the density distribution, and the local longitudinal area of low total pressure gas, ZLTP, near the model wall, whose appearance is due to the Cited by: 3.
Wall pressure fluctuations induced on a rigid wall by a turbulent boundary layer in supersonic regime are the subject of the present review. The sound and vibration of the structure subjected to the correlated fluctuating forces are modeled and predicted presuming the knowledge of a forcing function related to the wavenumber–frequency Cited by: 1.
Isobar map of the Rayleigh pressure ratio in the free mixing region and the shear layer. (The ratio refers to the local free-stream pressure) [ 8 ] The surprising similarity of results for the closure of two quite different cavities may be explained (with reservations) as follows: consider the “closed” free wake just before the critical point.
peak-to-peak spacing (s) of mm. The wall pressure fluctuations were measured in a modified turbulent boundary layer with riblets and the results were compared with smooth surface. It was found that the riblets reduce the root mean square amplitude of pressure fluctuation by about 4% as also the turbulence near the wall.
Poggie, J. and Smits, A.J., “Control of Pressure Fluctuations in the Reattachment Region of a Supersonic Shear Layer,” AIAA paper #, AIAA 3rd Shear Flow Control Conference, Orlando, Florida, July region, the impingement boundary layer, and the wall-jet region.
Flow solutions in the free jet and inviscid impingement regions provide the free-stream conditions for solution of the boundary layer equations needed to determine the wall shear stress in the impingement region. Farther from the stagnation point, as strong pressure. Response of a supersonic boundary layer to a compression corner By D.
Vandromme 1 AND O. Zeman 2 On the basis of direct numerical simulations of rapidly compressed turbulence, Zeman and Coleman () have developed a model to represent rapid directional compression contribution to the pressure dilatation term in the turbulent kinetic energy.
Contrariwise on injection the boundary layer is destabilized. At the high Mach number disturbances of two types is considered. The range of existence of the growing second-mode fluctuations is fairly narrow, as compared with the first mode.
At high supersonic regimes. The separated shear layer with an inflection point in the velocity profile is inherently unstable, and when this hits the body at the reattachment point selective amplification of the disturbances takes place, and this would cause the surface pressure to fluctuate in the flow separation region.
The point of reattachment could be shifting to Author: R. Mehta. In general, the rapid expansion was found to distort the initial mean velocity and turbulence fields in the shear layer, in a manner similar to that in rapidly expanded, attached supersonic boundary layers; namely, two distinct regions were found in the initial shear layer: an outer region, where the turbulent fluctuations are quenched Cited by: Supersonic Turbulent Flow Reattachment Downstream of a Two-Dimensional Backstep, AIAA Paper No.
C.; Page, R. Reda] on *FREE* shipping on qualifying : Reda, D. C.; Page, R. Mancinelli, Matteo Di Marco, Alessandro and Camussi, Roberto Multivariate and conditioned statistics of velocity and wall pressure fluctuations induced by a jet interacting with a flat plate.
Journal of Fluid Mechanics, Vol. p. CrossRef; Google ScholarCited by: TPIV measurements were acquired in three different volumetric regions throughout this flow, including two regions in the separated shear layer and one in the high-speed portion of the trailing wake, with a large ensemble of measurement volumes (approximately ) acquired in each region.
The hydrodynamic pressure fluctuations that occur on the solid surface beneath a turbulent boundary layer are a common source of flow noise. This paper reports multipoint surface pressure fluctuation measurements in water beneath a high-Reynolds-number turbulent boundary layer with wall injection of air to reduce skin-friction drag.
The experiments were conducted in the U.S. Navy’s Large Cited by: 5. In their concluding remarks, Brown & Roshko (, pp. 23–11) wrote, “A large, wave-like, structure, which increases in scale with distance from the origin of the shear layer is an essential feature of the uniform or variable density free shear layer at low Mach numbers.” This statement would have profound consequences in the Author: Dimitri Papamoschou, Morteza Gharib.
defined spectral peaks ofthe velocity fluctuations in the oscillating shear layer; and the pressure fluctuations at the impingement (downstream) comer ofthe cavity. The frequencies of these peaks show stage-like characteristics when either the inflow velocity U or the impingement length L is varied.
lems. Further, the wall-pressure eld is coupled to velocity uctuations across the entire domain via a Poisson equation, and the wall-parallel gradient in wall-pressure is directly proportional to the ux of vorticity from the wall (Koumoutsakos ).
As a result, an improved understanding of the wall-pressure eld can also contribute signi cantly to.An experimental investigation of large scale instabilities in a low Reynolds number two-stream supersonic shear layer. DENNIS No Access The dynamics and control of fluctuating pressure loads in the reattachment region of a supersonic free shear layer.
J. POGGIE An experimental study of a cold-wall hypersonic boundary layer. KUNG-MING.T1 - Flow reattachment and vortex re-formation on oscillating low-aspect-ratio wings. AU - Vardaki, E.
AU - Wang, Zhijin. AU - Gursul, I. PY - /6. Y1 - /6. N2 - Effects of small-amplitude wing oscillations on flow reattachment and vortex re-formation in the poststall region were studied by: