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Relevant bibliographies by topics / Convecting Freestream Vortex

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Journal articles
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Conference papers

Academic literature on the topic 'Convecting Freestream Vortex'

Author: Grafiati

Published: 6 September 2023

Last updated: 31 July 2025

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Journal articles on the topic "Convecting Freestream Vortex"

1

Green, R. B., and R. A. McD Galbraith. "Dynamic stall vortex convection: thoughts on compressibility effects." Aeronautical Journal 100, no. 999 (1996): 367–72. http://dx.doi.org/10.1017/s0001924000066902.

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AbstractThis paper considers the convection of the dynamic stall vortex. A brief discussion of existing data is given. A comparison of two sets of data from different experimental facilities is then presented, and it is indicated that an important anomaly exists concerning the behaviour of the dynamic stall vortex. It emerges that freestream Mach number is the only parameter that can account for the observed differences. The importance of this parameter is then discussed in the context of vorticity flux from the aerofoil surface.

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2

Zhang, X. "Turbulence Measurements of a Longitudinal Vortex Generated by an Inclined Jet in a Turbulent Boundary Layer." Journal of Fluids Engineering 120, no. 4 (1998): 765–71. http://dx.doi.org/10.1115/1.2820736.

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A longitudinal vortex in a flat-plate turbulent boundary layer was examined in a wind tunnel experiment using Laser Doppler Anemometry. The vortex was produced by an inclined round jet (D = 14 mm) in the turbulent boundary layer (δ0.99 ≈ 25 mm). The jet nozzle was positioned at pitch and skew angles of 45 deg to the oncoming stream, and the jet speed ratios (jet speed/freestream flow speed) were 0.5, 1.0, and 1.5. The flow was characterized by embedded vortices, induced high turbulent kinetic energy peak, local areas of high primary shear stress, and negative shear stress. Two types of normal

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3

Lin, San-Yin, Sheng-Chang Shih, and Jen-Jiun Hu. "Dissipation Improvement of MUSCL Scheme for Computational Aeroacoustics." Journal of Mechanics 17, no. 1 (2001): 39–47. http://dx.doi.org/10.1017/s1727719100002409.

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ABSTRACTAn upwind finite-volume scheme is studied for solving the solutions of two dimensional Euler equations. It based on the MUSCL (Monotone Upstream Scheme for Conservation Laws) approach with the Roe approximate Riemann solver for the numerical flux evaluation. First, dissipation and dispersion relation, and group velocity of the scheme are derived to analyze the capability of the proposed scheme for capturing physical waves, such as acoustic, entropy, and vorticity waves. Then the scheme is greatly enhanced through a strategy on the numerical dissipation to effectively handle aeroacousti

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4

Chung, Kung-Ming, Kao-Chun Su, and Keh-Chin Chang. "The Effect of Vortex Generators on Shock-Induced Boundary Layer Separation in a Transonic Convex-Corner Flow." Aerospace 8, no. 6 (2021): 157. http://dx.doi.org/10.3390/aerospace8060157.

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Deflected control surfaces can be used as variable camber control in different flight conditions, and a convex corner resembles a simplified configuration for the upper surface. This experimental study determines the presence of passive vortex generators, VGs (counter-rotating vane type), on shock-induced boundary layer separation for transonic convex-corner flow. The mean surface pressure distributions in the presence of VGs for h/δ = 0.2 and 0.5 are similar to those for no flow control. If h/δ = 1.0 and 1.5, there is an increase in the amplitude of the mean surface pressure upstream of the c

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5

Yao, Hua-Dong, Zhongjie Huang, Lars Davidson, Jiqiang Niu, and Zheng-Wei Chen. "Blade-Tip Vortex Noise Mitigation Traded-Off against Aerodynamic Design for Propellers of Future Electric Aircraft." Aerospace 9, no. 12 (2022): 825. http://dx.doi.org/10.3390/aerospace9120825.

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We study noise generation at the blade tips of propellers designed for future electric aircraft propulsion and, furthermore, analyze the interrelationship between noise mitigation and aerodynamics improvement in terms of propeller geometric designs. Classical propellers with three or six blades and a conceptual propeller with three joined dual-blades are compared to understand the effects of blade tip vortices on the noise generation and aerodynamics. The dual blade of the conceptual propeller is constructed by joining the tips of two sub-blades. These propellers are designed to operate under

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6

Yokota, Sho, Keisuke Asai, and Taku Nonomura. "Instability of Separated Shear Layer around Levitated Freestream-Aligned Circular Cylinder." Physics of Fluids, May 11, 2022. http://dx.doi.org/10.1063/5.0091044.

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In the present study, the characteristics of the shear layer around a freestream-aligned circular cylinder and the relationship between the shear layer motion and the aerodynamic force were investigated under supportless condition. The 0.3-m magnetic suspension and balance system (MSBS) was employed and experiments were conducted without a mechanical supporting device. Velocity fields were measured using particle image velocimetry with a sufficient temporal and spatial resolution and high-frequency velocity fluctuations caused by small Kelvin-Helmholtz (KH) vortices were captured. The power sp

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7

McAuliffe, Brian R., and Metin I. Yaras. "Numerical Study of Turbulent-Spot Development in a Separated Shear Layer." Journal of Turbomachinery 130, no. 4 (2008). http://dx.doi.org/10.1115/1.2812948.

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The development of turbulent spots in a separation bubble under elevated freestream turbulence levels is examined through direct numerical simulation. The flow Reynolds number, freestream turbulence level, and streamwise pressure distribution are typical of the conditions encountered on the suction side of low-pressure turbine blades of gas-turbine engines. Based on the simulation results, the spreading and propagation rates of the turbulent spots and their internal structure are documented, and comparisons are made to empirical correlations that are used for predicting the transverse growth a

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8

Fukuma, Akitomo, Manato Kawai, Nini Furukawa, et al. "Fluid–acoustic interactions around an expanding pipe with orifice plates." Physics of Fluids 36, no. 3 (2024). http://dx.doi.org/10.1063/5.0193029.

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Expanding pipes with orifice plates are often utilized as silencers for fluid machinery. However, intense tonal sounds can be generated from a flow through such expanding pipes. To clarify the mechanism of tonal sound from a flow through a circular expanding pipe with two orifice plates and the conditions for intense acoustic radiation, the flow and acoustic fields are directly solved based on the compressible Navier–Stokes equations. Phase-averaged flow fields indicate the occurrence of periodic vortex shedding in the free shear layers of the expanding pipe, resulting in acoustic radiation. T

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9

A., Rashid, and Hasan N. "Vortex-Shedding Suppression in Mixed Convective Flow past a Heated Square Cylinder." International Journal of Mechanical, Industrial and Aerospace Sciences 4.0, no. 6 (2011). https://doi.org/10.5281/zenodo.1334389.

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The present study investigates numerically the phenomenon of vortex-shedding and its suppression in twodimensional mixed convective flow past a square cylinder under the joint influence of buoyancy and free-stream orientation with respect to gravity. The numerical experiments have been conducted at a fixed Reynolds number (Re) of 100 and Prandtl number (Pr) of 0.71, while Richardson number (Ri) is varied from 0 to 1.6 and freestream orientation, α, is kept in the range 0o≤ α ≤ 90o, with 0o corresponding to an upward flow and 90o representing a cross-flow scenario, respectively. The continuity,

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10

Vikramaditya, N. S., and M. Viji. "Mach Number Effect on Symmetric and Antisymmetric Modes of Base Pressure Fluctuations." Journal of Fluids Engineering 141, no. 2 (2018). http://dx.doi.org/10.1115/1.4040928.

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An experimental study aimed at evaluating the influence of Mach number on the base pressure fluctuations of a cylindrical afterbody was performed over a wide range of Mach numbers from subsonic to supersonic speeds. Time-averaged results indicate that the coefficient of base pressure drops with the increase in the freestream Mach number at subsonic speeds and increases at supersonic Mach numbers. The coefficient of root-mean-square of the pressure fluctuations follows a decreasing trend with the increase in the Mach number. Examination of the spectra reveals different mechanisms dominate the p

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Dissertations / Theses on the topic "Convecting Freestream Vortex"

1

Vinod, Kumar B. G. "Co-operative Destabilization of a Flat Plate Boundary Layer by a Free Stream Convecting Vortex and Wall Suction/Blowing." Thesis, 2007. https://etd.iisc.ac.in/handle/2005/4627.

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The stability of wall bounded shear layer at subcritical Reynolds number disturbed by a freestream convecting vortex and unsteady suction/blowing at the wall was studied. A counterclockwise line vortex was convected parallel to the plate in the direction of the free-stream, slower than the free-stream velocity and well outside the boundary layer. Simultaneously, unsteady periodic suction/blowing of the identical uid was introduced near the leading edge on the plate through a narrow slit. The incompressible unsteady problem was modelled using the vorticity stream function formulation with appro

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Conference papers on the topic "Convecting Freestream Vortex"

1

Morse, Daniel R., and James A. Liburdy. "Dynamic Characteristics of Flow Separation From a Low Reynolds Number Airfoil." In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37083.

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This study examines the generation of large scale vortices caused by flow separation from a flat wing at various angles of attack. Time-resolved particle image velocimetry is used to determine the evolution and convective characteristics of the large scale structures. A rectangular airfoil with aspect ratio of 0.5 is used and data are collected at a Reynolds number of 23,500, for angles of attack from 0° to 20°. Data consists of two dimensional velocity fields obtained at 500 Hz located at the airfoil centerline. The region of interest is near the separation point but fields of view extend ove

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2

Morse, Daniel R., and James A. Liburdy. "Vortex Detection and Characterization in Low Reynolds Number Separation." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-43011.

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This study focuses on the detection and characterization of vortices in low Reynolds number separation flow over the elliptical leading edge of a flat plate airfoil. Velocity fields were obtained using Time Resolved Particle Image Velocimetry (TRPIV). The Reynolds number based on chord length ranged from 14,700 to 66,700. Experiments were performed for velocities of 1.1, 2.0 and 5.0 m/s and angles of attack of 14°, 16°, 18° and 20°. These velocities correspond to chord length Reynolds numbers of 1.47×104, 2.68×104, and 6.70×104, respectively. A local swirl calculation was used to determine reg

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3

Radomsky, R. W., and K. A. Thole. "High Freestream Turbulence Effects on Endwall Heat Transfer for a Gas Turbine Stator Vane." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0201.

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High freestream turbulence along a gas turbine airfoil and strong secondary flows along the endwall have both been reported to significantly increase convective heat transfer. This study superimposes high freestream turbulence on the naturally occurring secondary flow vortices to determine the effects on the flowfield and the endwall convective heat transfer. Measured flowfield and heat transfer data were compared between low freestream turbulence levels (0.6%) and combustor simulated turbulence levels (19.5%) that were generated using an active grid. These experiments were conducted using a s

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4

McAuliffe, B. R., and M. I. Yaras. "Numerical Study of Turbulent Spot Development in a Separated Shear Layer." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27604.

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The development of turbulent spots in a separation bubble under elevated freestream turbulence levels is examined through direct numerical simulation. The flow Reynolds number, freestream turbulence level, and streamwise pressure distribution are typical of the conditions encountered on the suction side of low-pressure turbine blades of gas-turbine engines. Based on the simulation results, the spreading and propagation rates of the turbulent spots and their internal structure are documented, and comparisons are made to empirical correlations that are used for predicting the transverse growth a

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5

Hossain, Mohammad A., Robin Prenter, Ryan K. Lundgreen, Ali Ameri, James W. Gregory, and Jeffrey P. Bons. "Experimental and Numerical Investigation of Sweeping Jet Film Cooling." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64479.

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A companion experimental and numerical study was conducted of the performance of a row of 5 sweeping jet (SJ) film cooling holes consisting of conventional curved fluidic oscillators with an aspect ratio (AR) of unity and a hole spacing of P/D = 8.5. Adiabatic film effectiveness (η), thermal field (θ), convective heat transfer coefficient (h) and discharge coefficient (CD) were measured at two different freestream turbulence levels (Tu = 0.4% and 10.1%) and four blowing ratios (M = 0.98, 1.97, 2.94 and 3.96) at a density ratio (DR) of 1.04 and hole Reynolds number of ReD = 2800. Adiabatic film

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6

Khalatov, A. "Improved Approach to an Endwall Heat Transfer Analysis: A Linear Guide Vane and a Curved Duct." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-293.

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This paper consists of two sections. The first section of the paper illustrates successful application of the improved approach developed by author to the endwall heat transfer data analysis in a low speed linear guide vane and in a curved duct. Effects of a three dimensional turbulent flow, a horseshoe vortex, a passage vortex, as well as an entry boundary layer thickness have been considered in both passages and as a result the common experimental correlation on a local heat transfer have been derived for the H/t = 1.0 ratio. All affected factors are presented as a superposition of the linea

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