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Wednesday, July 15, 2020 | History

3 edition of Hot film wall shear instrumentation for compressible boundary layer transition research found in the catalog.

Hot film wall shear instrumentation for compressible boundary layer transition research

Steven P. Schneider

Hot film wall shear instrumentation for compressible boundary layer transition research

by Steven P. Schneider

  • 266 Want to read
  • 31 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Hot-wire anemometer.,
  • Shear (Mechanics)

  • Edition Notes

    Statementprincipal investigator: Steven P. Schneider.
    Series[NASA contractor report] -- NASA CR-191360., NASA contractor report -- NASA CR-191360.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14693401M

    An experimental study of wall shear stress in an accelerating flow of water in a pipe ramping between two steady turbulent flows has been undertaken in a large-scale experimental facility. Ensemble averaged mean and r.m.s. of the turbulent fluctuations of wall shear stresses have been derived from hot-film measurements from many repeated runs. SHEAR WALL. Columns are compression elements where as shear wall is compression as well as shear resisting elements. A shear wall is a vertical structural element that resists lateral forces in the plane of the wall through shear and bending. Shear walls are usually provided along both length and width of buildings.

    Fig. 2 Visualization of laminar-turbulent transition by shear stress sensitive liquid crystals at different flow velocities, angle of attack α = 3º, LC initialization along the flow In the figure 3 the results of visualization of the boundary layer transition at different angles of attack at the flow velocity V . 99% Thermal Boundary Layer thickness. The thermal boundary layer thickness,, is the distance across a boundary layer from the wall to a point where the flow temperature has essentially reached the 'free stream' temperature,.This distance is defined normal to the wall in the thermal boundary layer thickness is customarily defined as the point in the boundary layer,, where the.

    Previous research indicates that the problem of boundary layer transition visualization on metal models in wind tunnels (WT) which is a fundamental question in experimental aerodynamics is not solved yet. In TsAGI together with Khristianovich Institute of Theoretical and Applied Mechanics (ITAM) a method of shear stress sensitive liquid crystals (LC) which allows flow visualization was proposed. For instance, researchers investigated the unsteady boundary layer behavior on the first stage stator using arrays of surface-mounted hot-film sensors to characterize the unsteady wall shear stress. The vane boundary layer development was strongly influenced by the incoming rotor wakes.


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Hot film wall shear instrumentation for compressible boundary layer transition research by Steven P. Schneider Download PDF EPUB FB2

Hot Film Wall Shear Instrumentation for Compressible Boundary Layer Transition Research?' I Principal Investigator: Steven P. Schneider Assistant Professor of Aerodynamics School of Aeronautics and Astronautics Purdue University West Lafayette, IN Period Covered: 1/1/91 to 11/1/92 (NASA-CRAO) ri_T FILM WALL SHEA._ I'ISTr.

Get this from a library. Hot film wall shear instrumentation for compressible boundary layer transition research. [Steven P Schneider; United States. Hot Film Wall Shear Instrumentation for Boundary Layer Transition Research: Final Report for NASA Grant NAG-I Steven P.

Schneider Assistant Professor of Aerodynamics School of Aeronautical and Astronautical Engineering Purdue University J Abstract Measurements of the performance of hot-film wall-shear sensors.

Measurements of the performance of hot-film wall-shear sensors were performed to aid development of improved sensors. The effect of film size and substrate properties on the sensor performance was quantified through parametric studies carried out both electronically and in a shock tube.

The results show that sensor frequency response increases with decreasing sensor size, while at the same Author: Steven P. Schneider. In this letter we present a novel wall shear stress measurement technique for a turbulent boundary layer using sandwiched hot-film sensors.

Under certain conditions, satisfactory results can be obtained using only the heat generated by one of the hot-film and a Cited by: 3. Instantaneous streamwise fluctuations of the wall shear stress have been measured using a hot-element probe in a thick axisymmetric turbulent boundary layer on a cylinder aligned parallel to the flow.

The measurements were made at a momentum-thickness Reynolds number R θ = and a ratio of boundary-layer thickness to cylinder radius of δ. Wall shear stress data obtained with a floating element device are presented for a fully developed turbulent boundary layer on a rough (cast) surface, and for boundary-layer transition on a smooth wall.

Comparisons of the data with estimates of the wall shear stress obtained from indirect techniques in common use show considerable differences. Furthermore the technique is not only applicable to laminar boundary layers, but also to turbulent boundary layers. However, measuring the wall-shear stress in a turbulent boun- dary layer requires a smaller hot spot, to keep the thermal boundary layer within the viscous sublayer of the hydrodynamic turbulent boundary layer.

Starting from fundamentals of classical stability theory, an overview is given of the transition phenomena in subsonic, wall-bounded shear flows. At first, the consideration focuses on elementary small-amplitude velocity perturbations of laminar shear layers, i.e.

instability waves, in the simplest. turbulent transition. Compressible boundary layer transition study is very important in the design of future hypersonic vehicles. Various works carried out on incompressible and compressible boundary layers relevant to our present effort have been discussed in this paper.

2 Survey of primary and secondary instability studies in boundary layers. Get this from a library. Hot film wall shear instrumentation for boundary layer transition research. [Steven P Schneider; United States. National Aeronautics and Space Administration.]. The interaction of disturbance modes behind an isolated cylindrical roughness element in a laminar boundary layer is investigated by means of hot-film anemometry and particle image velocimetry in.

The linear stability of inviscid compressible shear layers is studied. When the layer develops at the vicinity of a wall, the two parallel flows can have a velocity of the same sign or of opposite signs. This situation is examined in order to obtain first hints on the stability of separated flows in the compressible regime.

The shear layer is described by a hyperbolic tangent profile for the. The streamwise velocity reduces in the outer part of the boundary layer due to compression, while it increases near the wall due to curvature, with a higher shape factor for the concave cases.

Schro¨der, Th.,“Hot Film Instrumentation of the Rotor for the DLR Transonic Turbine Test Facility,” IMT Area 3 Turbine Project Contract AER2-CT, Task A Tiedemann, M.,“Stator Wake Effects on the Boundary Layer Transition of a Transonic Turbine Rotor Blade,” “Eurotherm Seminar No.

55, Heat transfer in. Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of.

Shear Layer Stability Analysis in Later Boundary Layer Transition and from the later boundary layer transition and another one from flow field generated by the The adiabatic and the non-slipping conditions are enforced at the wall boundary on the flat plate.

Combined heat transfer and wall shear stress measurements on the inner wall of a fully developed turbulent air flow in a round pipe were presented in this paper.

The heat transfer was measured using a flush-mounted dual hot-film sensor composed of a non-electric conductive membrane sandwiched in between two thin nickel films. Asbik, O. Ansari, B. Zeghmati, Numerical study of boundary layer transition in flowing film evaporation on horizontal elliptical cylinder, Heat and Mass Transfer, /s, 41, 5, (), ().

Modeling Transition: New Scenarios, System Sensitivity and Feedback Control (J A Burns & J R Singler) Dynamics of Transitional Boundary Layers (C Lee & S Chen) Continuous Mode Transition (P Durbin & T Zaki) Transition in Wall-Bounded Shear Flows: The Role of Modern Stability Theory (P J Schmid) A Framework for Control of Fluid Flow (A Guégan.

Recent direct numerical simulation (DNS) results relating to the behavior of the fluctuating wall-shear stress τ w, r m s + in turbulent boundary layer flows are discussed.

This new compilation is motivated by a recent article [Wu and Moin, “Transitional and turbulent boundary layer with heat transfer,” Phys.

Flu ()], which indicates a need for clarification of the value.American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The water film streams, without interfacial shear stress, along a horizontal elliptical tube under the simultaneous effects of gravity, pressure gradients, and viscous forces.

Outside the boundary layer, the vapor-phase velocity is obtained from potential flow.