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T.a. Fox - One of the best experts on this subject based on the ideXlab platform.
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Fluid-Induced Loading of Cantilevered Circular Cylinders in a Low-Turbulence Uniform FLow. Part 2: Fluctuationg Loads on a Cantilever of Aspect Ratio 30
Journal of Fluids and Structures, 1993Co-Authors: T.a. Fox, G.s. WestAbstract:Part 2 presents details of an investigation into the fluctuating loads induced on a smooth, cantilevered circular cylinder with an aspect ratio of 30 immersed in a Low-Turbulence uniform fLow. Experiments were carried out in a wind tunnel at a Reynolds number of 4·4 × 104 and involved the measurement of fluctuating pressures and forces. Oil-fLow visualization was performed to determine the fLow pattern at the surface of the cylinder. The results reveal the nature of the disturbance induced by the fLow around the free-end of a cantilever and the full extent of the spanwise variation of fluctuating pressures and forces.
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FLUID-INDUCED LOADING OF CANTILEVERED CIRCULAR CYLINDERS IN A Low-Turbulence UNIFORM FLow - PART 3: FLUCTUATING LOADS WITH ASPECT RATIOS 4 TO 25
Journal of Fluids and Structures, 1993Co-Authors: T.a. Fox, C. J. ApeltAbstract:Abstract Part 3 of this study presents details of an investigation into the fluctuating pressures and loads induced on smooth, cantilevered circular cylinders immersed in a Low-Turbulence, uniform fLow. Experiments were carried out in a wind tunnel at a Reynolds number of 4·4 × 104 for aspect ratios in the range 4 to 25. R.m.s. pressures on the surface of the cylinder and r.m.s. lift and drag were measured, and the frequency content of the fluctuation was analysed. The results are consistent with the mean loading pattern presented in Part 1, particularly with regard to the existence of a significant aspect ratio of 13, and complete the data set for aspect ratios in the range 4 to 30.
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FLUID-INDUCED LOADING OF CANTILEVERED CIRCULAR CYLINDERS IN A Low-Turbulence UNIFORM FLow - PART 1: MEAN LOADING WITH ASPECT RATIOS IN THE RANGE 4 TO 30
Journal of Fluids and Structures, 1993Co-Authors: T.a. Fox, G.s. WestAbstract:Part 1 presents details of an investigation into the mean loading of smooth, cantilevered circular cylinders immersed in a Low-Turbulence uniform fLow. Experiments were performed in a wind tunnel at a Reynolds number of 4.4 x 104 for aspect ratios in the range 4 to 30. Mean surface pressures and vortex-shedding frequencies were measured, from which the local mean pressure drag and Strouhal number were calculated at various spanwise locations. The results reveal the extent of the disturbance induced by the fLow around the free-end of a cantilever and the existence of a significant aspect ratio of 13. See also the folLowing abstract.
G.s. West - One of the best experts on this subject based on the ideXlab platform.
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Fluid-Induced Loading of Cantilevered Circular Cylinders in a Low-Turbulence Uniform FLow. Part 2: Fluctuationg Loads on a Cantilever of Aspect Ratio 30
Journal of Fluids and Structures, 1993Co-Authors: T.a. Fox, G.s. WestAbstract:Part 2 presents details of an investigation into the fluctuating loads induced on a smooth, cantilevered circular cylinder with an aspect ratio of 30 immersed in a Low-Turbulence uniform fLow. Experiments were carried out in a wind tunnel at a Reynolds number of 4·4 × 104 and involved the measurement of fluctuating pressures and forces. Oil-fLow visualization was performed to determine the fLow pattern at the surface of the cylinder. The results reveal the nature of the disturbance induced by the fLow around the free-end of a cantilever and the full extent of the spanwise variation of fluctuating pressures and forces.
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FLUID-INDUCED LOADING OF CANTILEVERED CIRCULAR CYLINDERS IN A Low-Turbulence UNIFORM FLow - PART 1: MEAN LOADING WITH ASPECT RATIOS IN THE RANGE 4 TO 30
Journal of Fluids and Structures, 1993Co-Authors: T.a. Fox, G.s. WestAbstract:Part 1 presents details of an investigation into the mean loading of smooth, cantilevered circular cylinders immersed in a Low-Turbulence uniform fLow. Experiments were performed in a wind tunnel at a Reynolds number of 4.4 x 104 for aspect ratios in the range 4 to 30. Mean surface pressures and vortex-shedding frequencies were measured, from which the local mean pressure drag and Strouhal number were calculated at various spanwise locations. The results reveal the extent of the disturbance induced by the fLow around the free-end of a cantilever and the existence of a significant aspect ratio of 13. See also the folLowing abstract.
David Lentink - One of the best experts on this subject based on the ideXlab platform.
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A new Low-Turbulence wind tunnel for animal and small vehicle flight experiments.
Royal Society open science, 2017Co-Authors: Daniel Quinn, Anthony Watts, Tony Nagle, David LentinkAbstract:Our understanding of animal flight benefits greatly from specialized wind tunnels designed for flying animals. Existing facilities can simulate laminar fLow during straight, ascending and descending flight, as well as at different altitudes. However, the atmosphere in which animals fly is even more complex. FLow can be laminar and quiet at high altitudes but highly turbulent near the ground, and gusts can rapidly change wind speed. To study flight in both laminar and turbulent environments, a multi-purpose wind tunnel for studying animal and small vehicle flight was built at Stanford University. The tunnel is closed-circuit and can produce airspeeds up to 50 m s-1 in a rectangular test section that is 1.0 m wide, 0.82 m tall and 1.73 m long. Seamless honeycomb and screens in the airline together with a carefully designed contraction reduce centreline Turbulence intensities to less than or equal to 0.030% at all operating speeds. A large diameter fan and specialized acoustic treatment alLow the tunnel to operate at Low noise levels of 76.4 dB at 20 m s-1. To simulate high Turbulence, an active Turbulence grid can increase Turbulence intensities up to 45%. Finally, an open jet configuration enables stereo high-speed fluoroscopy for studying musculoskeletal control in turbulent fLow.
Tassos G. Karayiannis - One of the best experts on this subject based on the ideXlab platform.
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Low Turbulence natural convection in an air filled square cavity part i the thermal and fluid fLow fields
International Journal of Heat and Mass Transfer, 2000Co-Authors: Y.s. Tian, Tassos G. KarayiannisAbstract:Abstract An experimental study of Low level Turbulence natural convection in an air filled vertical square cavity was conducted. The dimensions of cavity were 0.75 m × 0.75 m × 1.5 m giving two-dimensional fLow. The hot and cold walls of the cavity were isothermal at 50 and 10°C, respectively, giving a Rayleigh number of 1.58 × 109. The temperature and velocity distribution was systematically measured at different locations in the cavity, and was nearly anti-symmetrical. An experimentally obtained contour plot of the thermal field and a vector plot of the air fLow in the cavity are reported for Low Turbulence natural convection in such cavities for the first time. The wall shear stress and the local and average Nusselt numbers are also presented. The Nusselt number compares well with previous results; the agreement on the velocity and temperature profiles at mid-height near the vertical walls is fair. Differences were found at mid-width and in the rate of velocity and temperature changes near the walls. The experiments were conducted with high accuracy. Therefore, the results can form experimental benchmark data and will be useful for CFD code validation.
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Low Turbulence natural convection in an air filled square cavity: Part II: the Turbulence quantities
International Journal of Heat and Mass Transfer, 2000Co-Authors: Y.s. Tian, Tassos G. KarayiannisAbstract:Abstract An experimental study of two-dimensional Low level Turbulence natural convection in an air filled vertical square cavity was conducted at a Ra number of 1.58 × 10 9 . Turbulence quantities including T ′ rms , u ′ rms , v ′ rms and Reynolds stress are presented. The fluid fLow was turbulent anisotropic wall shear fLow. It was in the Low Turbulence region with a base frequency of about 0.1–0.2 Hz. The power spectral densities moved to higher frequency along the fluid fLow. The temperature and velocity fluctuations were limited in the boundary layers along the solid walls and were not in Gaussian distribution. The results indicate that the temperature and the velocity components fluctuate separately.
H. L. Morgan - One of the best experts on this subject based on the ideXlab platform.
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Experimental Test Results of Energy Efficient Transport (EET) High-Lift Airfoil in Langley Low-Turbulence Pressure Tunnel
2002Co-Authors: H. L. MorganAbstract:This report describes the results of an experimental study conducted in the Langley Low-Turbulence Pressure Tunnel to determine the effects of Reynolds number and Mach number on the two-dimensional aerodynamic performance of the Langley Energy Efficient Transport (EET) High-Lift Airfoil. The high-lift airfoil was a supercritical-type airfoil with a thickness-to- chord ratio of 0.12 and was equipped with a leading-edge slat and a double-slotted trailing-edge flap. The leading-edge slat could be deflected -30 deg, -40 deg, -50 deg, and -60 deg, and the trailing-edge flaps could be deflected to 15 deg, 30 deg, 45 deg, and 60 deg. The gaps and overlaps for the slat and flaps were fixed at each deflection resulting in 16 different configurations. All 16 configurations were tested through a Reynolds number range of 2.5 to 18 million at a Mach number of 0.20. Selected configurations were also tested through a Mach number range of 0.10 to 0.35. The plotted and tabulated force, moment, and pressure data are available on the CD-ROM supplement L-18221.
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Experimental Test Results of the Energy Efficient Transport (EET) Flap-Edge Vortex Model in the Langley Low-Turbulence Pressure Tunnel
2002Co-Authors: H. L. MorganAbstract:This report presents the results of a test conducted in the Langley Low-Turbulence Pressure Tunnel to measure the fLow field properties of a flap-edge vortex. The model was the EET (Energy Efficient Transport) Flap-Edge Vortex Model, which consists of a main element and a part-span, single-slotted trailing-edge flap. The model surface was instrumented with several chordwise and spanwise rows of pressure taps on each element. The off-body fLow field velocities were to be measured in several planes perpendicular to the flap edge with a laser velocimetry system capable of measuring all three components in coincidence. However, due to seeding difficulties, the preliminary laser data did not have sufficient accuracy to be suitable for presentation; therefore, this report presents only the tabulated and plotted surface pressure data. In addition, the report contains a detail description of the model which can be used to generate accurate CFD grid structures.
