Relevant bibliographies by topics / Freestream velocity

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers

Academic literature on the topic 'Freestream velocity'

Author: Grafiati
Published: 4 June 2021
Last updated: 19 February 2022

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Journal articles on the topic "Freestream velocity"

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Thole, K. A., and D. G. Bogard. "High Freestream Turbulence Effects on Turbulent Boundary Layers." Journal of Fluids Engineering 118, no. 2 (June 1, 1996): 276–84. http://dx.doi.org/10.1115/1.2817374.

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High freestream turbulence levels significantly alter the characteristics of turbulent boundary layers. Numerous studies have been conducted with freestreams having turbulence levels of 7 percent or less, but studies using turbulence levels greater than 10 percent have been essentially limited to the effects on wall shear stress and heat transfer. This paper presents measurements of the boundary layer statistics for the interaction between a turbulent boundary layer and a freestream with turbulence levels ranging from 10 to 20 percent. The boundary layer statistics reported in this paper include mean and rms velocities, velocity correlation coefficients, length scales, and power spectra. Although the freestream turbulent eddies penetrate into the boundary layer at high freestream turbulence levels, as shown through spectra and length scale measurements, the mean velocity profile still exhibits a log-linear region. Direct measurements of total shear stress (turbulent shear stress and viscous shear stress) confirm the validity of the log-law at high freestream turbulence levels. Velocity defects in the outer region of the boundary layer were significantly decreased resulting in negative wake parameters. Fluctuating rms velocities were only affected when the freestream turbulence levels exceeded the levels of the boundary layer generated rms velocities. Length scales and power spectra measurements showed large scale turbulent eddies penetrate to within y+ = 15 of the wall.
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Fraser, C. J., and J. S. Milne. "Integral Calculations of Transitional Boundary Layers." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 200, no. 3 (May 1986): 179–87. http://dx.doi.org/10.1243/pime_proc_1986_200_113_02.

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A method is presented for the calculation of two-dimensional, incompressible, transitional boundary layers under small pressure gradient and moderate freestream turbulence conditions. Established integral techniques are used in conjunction with an intermittency weighted model of the transitional boundary layer, and empirical correlations are used to predict the onset and length of the transition region. The only input data required to compute the entire unseparated boundary layer are the ambient pressure and temperature, the freestream turbulence level and the freestream velocity distribution in a power law, or a polynomial form. Alternatively, the freestream velocity can be input in tabular form as a function of x. The computed integral parameters and mean velocity profiles are seen to compare favourably with present and other published experimental data.
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Matsunuma, Takayuki, and Takehiko Segawa. "Effects of Input Voltage and Freestream Velocity on Active Flow Control of Passage Vortex in a Linear Turbine Cascade Using Dielectric Barrier Discharge Plasma Actuator." Energies 13, no. 3 (February 9, 2020): 764. http://dx.doi.org/10.3390/en13030764.

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Passage vortex exists as one of the typical secondary flows in turbomachines and generates a significant total pressure loss and degrades the aerodynamic performance. Herein, a dielectric barrier discharge (DBD) plasma actuator was utilized for an active flow control of the passage vortex in a linear turbine cascade. The plasma actuator was installed on the endwall, 10 mm upstream from the leading edge of the turbine cascade. The freestream velocity at the outlet of the linear turbine cascade was set to range from UFS,out = 2.4 m/s to 25.2 m/s, which corresponded to the Reynolds number ranging from Reout = 1.0 × 104 to 9.9 × 104. The two-dimensional velocity field at the outlet of the linear turbine cascade was experimentally analyzed by particle image velocimetry (PIV). At lower freestream velocity conditions, the passage vortex was almost negligible as a result of the plasma actuator operation (UPA,max/UFS,out = 1.17). Although the effect of the jet induced by the plasma actuator weakened as the freestream velocity increased, the magnitude of the peak vorticity was reduced under all freestream velocity conditions. Even at the highest freestream velocity condition of UFS,out = 25.2 m/s, the peak value of the vorticity was reduced approximately 17% by the plasma actuator operation at VAC = 15 kVp-p (UPA,max/UFS,out = 0.18).
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Radomsky, R. W., and K. A. Thole. "Detailed Boundary Layer Measurements on a Turbine Stator Vane at Elevated Freestream Turbulence Levels." Journal of Turbomachinery 124, no. 1 (February 1, 2001): 107–18. http://dx.doi.org/10.1115/1.1424891.

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High freestream turbulence levels have been shown to greatly augment the heat transfer on a gas turbine airfoil. To better understand these effects, this study has examined the effects elevated freestream turbulence levels have on the boundary layer development along a stator vane airfoil. Low freestream turbulence measurements (0.6 percent) were performed as a baseline for comparison to measurements at combustor simulated turbulence levels (19.5 percent). A two-component LDV system was used for detailed boundary layer measurements of both the mean and fluctuating velocities on the pressure and suction surfaces. Although the mean velocity profiles appeared to be more consistent with laminar profiles, large velocity fluctuations were measured in the boundary layer along the pressure side at the high freestream turbulence conditions. Along the suction side, transition occurred further upstream due to freestream turbulence.
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Yaras, M. I. "An Experimental Study of Artificially-Generated Turbulent Spots Under Strong Favorable Pressure Gradients and Freestream Turbulence." Journal of Fluids Engineering 129, no. 5 (September 13, 2006): 563–72. http://dx.doi.org/10.1115/1.2717608.

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This paper presents experimental results on the internal flow structure of turbulent spots, and examines the sensitivity of this structure to streamwise acceleration rate and freestream turbulence. Measurements were performed on a flat plate, with two levels of freestream acceleration rate and three levels of freestream turbulence. The turbulent spots were generated artificially at a fixed distance from the test-surface leading edge, and the development of the spot was documented through hotwire measurements at three streamwise locations. The measurements were performed at multiple spanwise locations to allow observation of the three-dimensional spatial structure of the turbulent spot and the temporal evolution of this structure. Analysis of the perturbation velocity and rms velocity fluctuations provides insight into the variations of the streaky streamwise-velocity structure within the turbulent spot, with a focus on the effects of freestream acceleration rate and turbulence level.
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Wang, Qing, and Qijun Zhao. "Unsteady Aerodynamic Characteristics Simulations of Rotor Airfoil under Oscillating Freestream Velocity." Applied Sciences 10, no. 5 (March 6, 2020): 1822. http://dx.doi.org/10.3390/app10051822.

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The dynamic stall characteristics of rotor airfoil are researched by employing unsteady Reynolds-Averaged Navier-Stokes (RANS) method under oscillating freestream velocity conditions. In order to simulate the oscillating freestream velocity of airfoil under dynamic stall conditions, the moving-embedded grid method is employed to simulate the oscillating velocity. By comparing the simulated dynamic stall characteristics of two-dimensional airfoil and three-dimensional rotor, it is indicated that the dynamic stall characteristics of airfoil under oscillating freestream velocity reflect the actual dynamic stall characteristics of rotor airfoil in forward flight more accurately. By comparing the simulated results of OA209 airfoil under coupled freestream velocity/pitching oscillation conditions, it is indicated that the dynamic stall characteristics of airfoil associate with the critical value of Cp peaks (i.e., the dynamic stall characteristics of OA209 airfoil would be enhanced when the maximum negative pressure is larger than −1.08, and suppressed when this value is smaller than −1.08). By comparing the characteristics of vortices under different oscillating velocities, it indicates that the dissipation rate of leading edge vortex presents as exponent characteristics, and it is not sensitive to different oscillating velocities.
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Dechant, Lawrence J. "Effect of Freestream Velocity Disturbances on Hypersonic Vehicles." Journal of Spacecraft and Rockets 49, no. 4 (July 2012): 751–56. http://dx.doi.org/10.2514/1.a32113.

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Heathcote, S., D. Martin, and I. Gursul. "Flexible Flapping Airfoil Propulsion at Zero Freestream Velocity." AIAA Journal 42, no. 11 (November 2004): 2196–204. http://dx.doi.org/10.2514/1.5299.

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Carlson, Bailey, Al Habib Ullah, and Jordi Estevadeordal. "Experimental Investigation of Vortex-Tube Streamwise-Vorticity Characteristics and Interaction Effects with a Finite-Aspect-Ratio Wing." Fluids 5, no. 3 (July 24, 2020): 122. http://dx.doi.org/10.3390/fluids5030122.

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An experimental study is conducted to analyze a streamwise-oriented vortex and investigate the unsteady interaction with a finite-aspect-ratio wing. A pressurized vortex tube is used to generate streamwise vortices in a wind tunnel and the resulting flow behavior is analyzed. The vortex tube, operated at various pressures, yields flows that evolve downstream under several freestream wind tunnel speeds. Flow measurements are performed using two- and three- dimensional (2D and 3D) particle image velocimetry to observe vortices and their freestream interactions from which velocity and vorticity data are comparatively analyzed. Results indicate that vortex velocity greater than freestream flow velocity is a primary factor in maintaining vortex structures further downstream, while increased supply pressure and reduced freestream velocity also reduce vortex dissipation rate. The generated streamwise-oriented vortex is also impinged on a finite-aspect-ratio airfoil wing with a cross-section of standard NACA0012 airfoil. The wingtip-aligned vortex is shown to investigate the interaction of the streamwise vortex and the wingtip vortex region. The results indicate that the vorticity at the high vortex-tube pressure has a significant effect on the boundary layer of airfoil.
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Hoffmann, J. A., and K. Mohammadi. "Velocity Profiles for Turbulent Boundary Layers Under Freestream Turbulence." Journal of Fluids Engineering 113, no. 3 (September 1, 1991): 399–404. http://dx.doi.org/10.1115/1.2909509.

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Correlations for changes of skin friction coefficients (Δcf) and wake parameters (ΔΠ), relative to the low freestream turbulence condition, are presented for the case of turbulent boundary layers under freestream turbulence with zero and adverse pressure gradients. The turbulent boundary layers were evaluated on a plate in a wind tunnel using a monoplane rod set turbulence generator; comparisons were also made using the data of several other investigators. The results, which define the velocity profiles within the boundary layers, were found to collapse for a large range of the pressure gradient parameter.
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Dissertations / Theses on the topic "Freestream velocity"

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Polanka, Marcus Damian. "Detailed film cooling effectiveness and three component velocity field measurements on a first stage turbine vane subject to high freestream turbulence /." Digital version accessible at:, 1999. http://wwwlib.umi.com/cr/utexas/main.

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Scheibe, Oskar. "Modelling of Heat Transfer for Convection-boosted Flat Vertical Radiator Surfaces : An investigation of how heat transfer is influenced by radiator height and freestream air velocity." Thesis, KTH, Strömnings- och klimatteknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-220138.

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In this thesis, a calculation model is created to study a theoretical radiator-like configuration, consisting of a flat vertical plate heated with a constant capacity rate. This lumped capacitance model is partly created to more theoretically look at radiators with add-on-fans, but also to in such a setting look at fundamental heat transfer relationships. System heat transfer is studied for various heights, H (m), and freestream velocities, u (m/s). These results are then subject to validation, where comparison is made with values derived from two relevant reference studies. It is found that polynomial fits well describe the results obtained from calculation. The relationships for heat transfer Q (W), heat flux q (W/m2) thus become: 𝑄(𝐻,𝑢) = 𝑎00 + 𝑎01𝑢 + 𝑎10𝐻 + 𝑎11𝐻𝑢 + 𝑎02𝑢2 (W) 𝑞(𝐻,𝑢) =𝑄/𝐻= 𝑎00𝐻-1 + 𝑎01𝐻-1𝑢 + 𝑎10 + 𝑎11𝑢 + 𝑎02𝐻-1𝑢2 (W/m2) For these relationships, polynomial coefficients 𝑎00, 𝑎01, 𝑎10, 𝑎11 and 𝑎02 are found for three temperature set-ups of system supply and return temperature at zero freestream velocity: 55/45, 45/35 and 35/25 (°C). These values are chosen as they correspond to standard temperatures for low-temperature heating set-ups. Model validation is successful for the case of natural convection (u = 0), whereas difficulties are encountered for the cases of mixed and forced convection. Reasons for these difficulties are discussed and it is concluded that there is a need for more experimental studies of flat vertical plates with non-isothermal wall temperature profiles.
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Gharali, Kobra. "Pitching airfoil study and freestream effects for wind turbine applications." Thesis, 2013. http://hdl.handle.net/10012/7833.

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A Horizontal Axis Wind Turbine (HAWT) experiences imbalanced loads when it operates under yaw loads. For each blade element of the aerodynamically imbalanced rotor, not only is the angle of attack unsteady, but also the corresponding incident velocity, a fact usually unfairly ignored. For the unsteady angle of attack, a pitch oscillating airfoil has been studied experimentally and numerically when 3.5×10⁴
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"The Effect of a Splitter Plate on the Flow around a Surface-Mounted Finite Circular Cylinder." Thesis, 2011. http://hdl.handle.net/10388/ETD-2011-09-171.

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Splitter plates are passive flow control devices for reducing drag and suppressing vortex shedding from bluff bodies. Most studies of splitter plates involve the flow around an “infinite” circular cylinder, however, in the present study the flow around a surface-mounted finite-height circular cylinder, with a wake-mounted splitter plate, was studied experimentally in a low-speed wind tunnel using a force balance and single-component hot-wire anemometry. Four circular cylinders of aspect ratios AR = 9, 7, 5 and 3 were tested for a Reynolds number range of Re = 1.9×10^4 to 8.2×10^4. The splitter plates had lengths, relative to the cylinder diameter, of L/D = 1, 1.5, 2, 3, 5 and 7, thicknesses ranging from T/D = 0.10 and 0.15, and were the same height as the cylinder being tested. The cylinders were partially immersed in a flat-plate turbulent boundary layer, where the range of boundary layer thickness relative to the cylinder diameter was δ/D = 1.4 to 1.5. Measurements were made of the mean drag force coefficient, the Strouhal number at the mid-height position, and the Strouhal number and power spectra along the cylinder height. For all four finite circular cylinders, the splitter plates were effective at reducing the magnitude of the Strouhal number, and weakening or even suppressing vortex shedding, depending on the specific combination of AR and L/D. Compared to the case of an infinite circular cylinder, the splitter plate is less effective at reducing the mean drag force coefficient of a finite circular cylinder. The largest drag reduction was obtained for the cylinder of AR = 9 and splitter plates of L/D = 1 to 3, while negligible drag reduction occurred for the shorter cylinders.
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Books on the topic "Freestream velocity"

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James, VanFossen G., and United States. National Aeronautics and Space Administration., eds. Increased heat transfer to a cylindrical leading edge due to spanwise variations in the freestream velocity. [Washington, D.C.]: National Aeronautics and Space Administration, 1991.

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Conference papers on the topic "Freestream velocity"

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Heathcote, Sam, and Ismet Gursul. "Flexible Flapping Wing Propulsion at Zero Freestream Velocity." In 33rd AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3446.

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Parker, Ronald, Thomas Wakeman, Mathew MacLean, and Michael Holden. "Measuring Nitric Oxide Freestream Velocity Using Quantum Cascade Lasers at CUBRC." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-1329.

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Margason, Richard, and Jin Tso. "Jet to freestream velocity ratio computations for a jet in a crossflow." In International Powered Lift Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-4860.

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Gatlin, Gregory, and Robert McGhee. "Freestream velocity measurements and corrections for two-dimensional testing with splitter plates." In 14th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-2386.

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Wilson, Dennis E., and Anthony J. Hanford. "An Unsteady Velocity Formulation for the Edge of the Near-Wall Region." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-478.

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A phenomenological model is presented that relates freestream turbulence to the augmentation of stagnation-point surface flux quantities. The model requires the turbulence intensity, the longitudinal scale of the turbulence, and the energy spectra as inputs for the unsteady velocity at the edge of the near-wall viscous region. The form of the edge velocity contains both pulsations of the incoming flow and oscillations of the streamline. Incompressible results using a single fluctuating component are presented within the stagnation region of a two-dimensional cylinder. The time-averaged Froessling number is determined from the computations. These predictions are compared to existing incompressible experimental data. Additionally, the variations in the surface flux quantities with the longitudinal scale of the incoming freestream turbulence, the Reynolds number, and the freestream turbulence intensity are considered.
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Codoni, Joshua R., Erin M. Reed, James McDaniel, Hicham Alkandry, and Iain D. Boyd. "Planar Laser-Induced Fluorescence Velocity Measurements of Retropropulsion Jets in a Mach 12 Freestream." In 31st AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2810.

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Brookfield, J. M., I. A. Waitz, and J. Sell. "Wake Decay: Effect of Freestream Swirl." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-495.

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A study of the effects of freestream swirl on the decay characteristics of wakes shed from a rotating blade row is presented. The freestream swirl behind the rotor causes the wakes to skew tangentially, stretching the wakes as they are convected from the rotor to the stator. The effect of stretching on wake decay is illustrated using a simplified two-dimensional model. The model is described and the results are compared to 1) measurements from a two-dimensional cascade facility where no stretching or skewing of the wakes occurs, 2) solutions obtained using a three-dimensional, Reynolds-averaged Navier-Stokes solver, and 3) experimental wake measurements taken behind a low hub-to-tip ratio fan. For typical fan geometries with hub-to-tip ratios of approximately 0.5 and rotor-stator spacings of one to two rotor chord lengths, the wake can be stretched by over 50 percent. The stretching increases the mixing rate which leads to a reduction in the mean wake velocity deficit of approximately thirty percent and a widening of the wake of about fifteen percent. These effects account for much of the difference seen between cascade wake measurements and those taken behind rotating fan blade rows. It is therefore important to include such effects when using cascade data for prediction of fluid mechanic, acoustic, or structural phenomena associated with fan wakes. Finally, the study also suggests a potential for small (< 3 dB) reductions in wake-stator interaction noise through tailoring the fan loading distribution to produce particular span wise wake decay characteristics.
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Auchoybur, Kiran, and Robert J. Miller. "Design of Compressor Endwall Velocity Triangles." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57396.

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Near the endwalls of multi-stage compressor blade rows, there is a spanwise region of low momentum, high entropy fluid which develops due to the presence of annulus walls, leakage flows and corner separations. Off-design this region, known as the endwall flow region, often grows rapidly and in practice sets the compressor’s operating range. By contrast, over the operating range of the compressor, the freestream region of the flow is not usually close to its diffusion limit and has little effect on overall range. In light of these two distinct flow regions within a bladerow, this paper considers how velocity triangles in the endwall region should be designed to give a more balanced spanwise failure across the blade span. In the first part of the paper, the sensitivity of the operating flow range of a single blade row to variations in realistic multistage inlet conditions and endwall geometry is investigated. It is shown that the operating range of the blade row is largely controlled by the size and structure of the endwall ‘repeating stage’ inlet boundary layer and not the detailed local geometry within the blade row. In the second part of the paper the traditional design process is ‘flipped’. Instead of redesigning a blade’s endwall geometry to cope with a particular inlet profile into the blade row, the endwall region is redesigned in the multi-stage environment to ‘tailor’ the inlet profile into downstream blade rows. This is shown to allow an extra degree of freedom not usually open to the designer. This extra degree of freedom is exploited to balance freestream and endwall operating range, resulting in a compressor having an increased operating range of ∼20%. If this increased operating range is traded with reduced blade count, it is shown that a design efficiency improvement of Δη∼0.5% can be unlocked.
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Radomsky, R. W., and K. A. Thole. "Detailed Boundary Layer Measurements on a Turbine Stator Vane at Elevated Freestream Turbulence Levels." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0169.

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High freestream turbulence levels have been shown to greatly augment the heat transfer on a gas turbine airfoil. To better understand these effects, this study has examined the effects elevated freestream turbulence levels have on the boundary layer development along a stator vane airfoil. Low freestream turbulence measurements (0.6%) were performed as a baseline for comparison to measurements at combustor simulated turbulence levels (19.5%). A two-component LDV system was used for detailed boundary layer measurements of both the mean and fluctuating velocities on the pressure and suction surfaces. Although the mean velocity profiles appeared to be more consistent with laminar profiles, large velocity fluctuations were measured in the boundary layer along the pressure side at the high freestream turbulence conditions. Along the suction side, transition occurred further upstream due to freestream turbulence.
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Abedin, Mohammad Zoynal, and Toshihiro Tsuji. "Effects of Freestream on Thermally-Driven Boundary Layers Along a Heated Vertical Flat Plate." In 2010 14th International Heat Transfer Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ihtc14-22167.

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Time-developing thermally-driven boundary layers created by imposing aiding and opposing freestreams on the natural-convection boundary layer in water along a heated vertical flat plate have been examined with a direct numerical simulation. The numerical results reveal that, with a slight increase in freestream velocity, the transition to turbulence delays for aiding flow and quickens for opposing flow. This fact is linked to the experimental results indicating that heat transfer rates of the turbulent combined-convection boundary layer decrease for aiding flow and increase for opposing flow with increasing freestream velocity. In response, turbulence statistics obtained for aiding flow such as the intensities of velocity and temperature fluctuations, Reynolds shear stress and turbulent heat fluxes become smaller than those for the pure natural-convection boundary layer suggesting the way to laminarization of the boundary layer, while those for opposing flow are not much different from the observations for the pure natural-convection boundary layer. To improve the significance of the present numerical results, the association of turbulence statistics between time- and space-developing flows has been also investigated. Consequently, the numerical results for time-developing flow are converted to those for space-developing flow through the integral thickness of the velocity boundary layer for pure natural convection, and thus the regimes of boundary layer flows in water can be quantitatively assessed. Moreover, by visualizing the flow field of the combined-convection boundary layers, it is found that the long-drawn high- and low-speed fluid motions with weak fluctuations for aiding flow and the large scale fluid motions for opposing flow are more apparent than those for the pure natural-convection boundary layer.
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