3 edition of Turbulent heat flux measurements in a transitional boundary layer found in the catalog.
Turbulent heat flux measurements in a transitional boundary layer
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va
Written in English
|Statement||K.H. Sohn, K.B.M.Q. Zaman, and E. Reshotko.|
|Series||NASA technical memorandum -- 105623.|
|Contributions||Zaman, K. B. M. Q., Reshotko, E., United States. National Aeronautics and Space Administration.|
|The Physical Object|
|Number of Pages||118|
randturbulentboundarylayers JohnRichardThome 8avril JohnRichardThome (LTCM-SGM-EPFL) Heattransfer-Convection 8avril 1/ In both flow cases the laminar-turbulent transition takes place at M transitional and turbulent boundary layers. They confirmed by direct numerical simulation that.
Turbulent boundary layer Stanton number measurements are reported for a constant nominal wall temperature of 44°C at nominal free stream velocities of 6, 12, 28, 43, 58, and 66 m/s for the truncated cone surfaces with L/d o = 2 and L/d o = 4. These results are compared with companion hemisphere roughened surfaces at deliberately matched flow. A Transient Global Heat-Flux Measurements for High-Speed Flow over a Wall-Mounted Cylinder in a Shock Tube. Study of the Dynamics of Transitional Shock Wave-Boundary Layer Interactions using Optical Diagnostics Flow in the zones of separation of a turbulent boundary layer in front of a subsonic jet injected through a circular nozzle.
An experimental setup was designed, built and validated and heat transfer measurements were taken at a heat flux of kW/m 2 between Reynolds numbers of and 10 The boundary layer transition over a flat tilted plate has been studied by means of heat transfer measurements. A heat flux sensor has been developed, in order to measure the efficiency of convective heat transfer for various types of surfaces or flows. Its operation at constant temperature allows direct and fast measurements of heat flux. The present paper reports the .
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Lienhard, John H., V, "Heat transfer in flat-plate boundary layers: a correlation for laminar, transitional, and turbulent flow." Journal of Heat Transfer6 (June ): no.
doi / © Author(s)Author: John H. Lienhard. 1. Introduction. The boundary layer heat transfer increases significantly when laminar to turbulent transition occurs.
Especially, in turbomachines, where hot gases from the combustion chamber force an enormous heat flux to the turbine blades, it is of major importance to know this heat transfer by: However, in the numerical simulations of Kasagi et al.
 for turbulent boundary layer with iso-heat flux, negative values of the turbulent normal heat flux is also observed especially for. However, in larger flames and at a greater height, the radiative heat flux dominates.
The current study provides a comprehensive dataset for model validation, such as the higher-order temperature distribution, spectral radiance, direct measurement of convective heat flux in a vertical turbulent boundary layer flame.
Keywords: Boundary layer; Heat transfer; Turbines 1. Introduction The boundary layer heat transfer increases signiﬁ-cantly when laminar to turbulent transition occurs.
Es-pecially, in turbomachines, where hot gases from the combustion chamber force an enormous heat ﬂux to the turbine blades, it is of major importance to know this. Particle image velocimetry measurements of a transitional boundary layer under free stream turbulence - Volume - K.
Nolan, E. Walsh. Heat transfer and wall temperature effects in shock wave turbulent boundary layer interactions 30 December | Physical Review Fluids, Vol. 1, No. 8 Hysteresis phenomenon of hypersonic inlet at high Mach number.
Three variants of schlieren techniques are employed to investigate the development of second-mode instability waves in the hypersonic boundary layer of a slender cone in a reflected shock tunnel. First, a previously proposed technique using high frame rate (i.e., at least as high as the dominant instability frequency) schlieren visualization with a continuous light source is shown.
This work studies the development of a thermal boundary layer during the laminar-to-turbulent transition process over a concave surface. Direct numerical simulations are. The principal goal of the Hypersonic International Flight Research Experimentation (HIFiRE) flight 5 is to measure hypersonic boundary-layer transition on a three-dimensional body.
This paper presents measurements of heat flux and boundary-layer transition in the Boeing/U.S. Air Force Office of Scientific Research Mach-6 Quiet Tunnel. The transition from a laminar to turbulent boundary layer on a wing operating at low Reynolds numbers can have a large effect on its aerodynamic performance.
For a wing operating. Data for external, turbulent boundary-layer heat transfer have mainly been acquired in air flows. Water boundary layers have been measured, apparently, only by Žukauskas and Šlančiauskas and by Hollingsworth. Data for other liquids are even more limited, amounting to measurements in “transformer oil,” again by Žukauskas and coworkers.
Measurements were taken for two levels of free-stream disturbance— and percent. Turbulent Prandtl numbers for the transitional flow, computed from measured shear stress, turbulent heat flux, and mean velocity and temperature profiles, were less than unity.
Turbulence measurements for both momentum and heat transport are taken in a boundary layer over a flat recovery wall downstream of a concave wall (R = m). The boundary layer appears turbulent from the beginning of the upstream, concave wall and grows over the flat test wall downstream of the curved wall with negligible streamwise acceleration.
Abstract. Measurements of mean velocity and temperature, and of surface heat flux, have been made in a turbulent boundary layer on a heated convex surface of modest curvature (δ/R ∼).
The results show surprisingly large curvature effects on heat transfer: at the end of the curved plate the Stanton number fell by 18% of the predicted flat plate value; the. Heat transfer results are presented for laminar, transition, and turbulent boundary layers for a Mach number of with gas temperatures of K and K over a.
A very high frequency-responding thin film sensor system is developed and applied to measure mean and fluctuation value of heat flux rate about the hypersonic flow over two slender cones.
Experiments are having performed in a piston shot tunnel at Mach number 6. Measurements are asymmetric transition of the boundary layer over the slender cone. The time averaged heat flux and the heat flux.
The progressive organization of the boundary layer during the transition process is more obvious if one con-siders the intensity profiles of the temperature and velocity fluctuations. Here again, the thickness of the fluctuat-ing boundary layer at high heat flux during transition is smaller than the turbulent one at low temperature in .
We report on our direct numerical simulation of an incompressible, nominally zero-pressure-gradient flat-plate boundary layer from momentum thickness Reynolds number 80– Heat transfer between the constant-temperature solid surface and the free-stream is also simulated with molecular Prandtl number Pr=1.
Skin-friction coefficient and other boundary layer. Measurements from transitional, heated boundary layers along a concave-curved test wall are presented and discussed. A boundary layer subject to low free-stream turbulence intensity (FSTI), which contains stationary streamwise (Gortler) vortices, is documented.
The low FSTI measurements are followed by measurements in boundary layers subject to high (initially. It is generally accepted that the separation location can be identified where the non-dimensional heat-flux, St, slope abruptly increases for a turbulent boundary layer and decreases for a .As part of the Coupled Boundary Layer Air‐Sea Transfer (CBLAST) experiment, flights were conducted to measure turbulent fluxes in the high‐wind boundary layer of hurricanes.
Here we present the first field observations of sensible heat and enthalpy flux for 10m wind speeds to 30 ms −1. The analyses indicate no statistically significant.Measurements from heated boundary layers along a concave-curved test wall subject to high (initially 8 percent) free-stream turbulence intensity and strong (K = (ν/U ∞ 2) dU ∞ /dx) as high as 9 × 10 −6) acceleration are presented and ions for the experiments were chosen to roughly simulate those present on the downstream half of the pressure side of a gas turbine .