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Freestream

About: Freestream is a research topic. Over the lifetime, 3428 publications have been published within this topic receiving 56147 citations.


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Journal ArticleDOI
TL;DR: In this paper, the use of rear cavities at the base of a square-back Ahmed body has been experimentally evaluated as a passive control device under cross-wind conditions with yaw angles β ≤ 10 °, by means of pressure, force and velocity measurements.

25 citations

Proceedings ArticleDOI
01 Jul 1992
TL;DR: The ASU Transition Research Facility is commonly called the ASU Unsteady Wind Tunnel because of its unsteady-flow capability as mentioned in this paper, which is a closed return tunnel within which oscillatory flows of air can be generated for the study of low-speed aerodynamics.
Abstract: The ASU Transition Research Facility is commonly called the ASU Unsteady Wind Tunnel because of its unsteady-flow capability. This facility has been in operation since 1988. It is a closed return tunnel within which oscillatory flows of air can be generated for the study of unsteady problems in low-speed aerodynamics. Because it also has excellent low-turbulence characteristics, it has been used principally as a boundary-layer transition research facility. The wind tunnel is described along with its unsteady calibration data. Examples of freestream turbulence and boundary-layer transition measurements are given.

25 citations

Journal ArticleDOI
TL;DR: In this article, the authors performed numerical simulations of leading-edge acoustic receptivity for a plate with a modie ed-superelliptic leading edge and found that the slope of the leading edge receptivity coefficient vs angle of incidence of the impinging wave is less than 1 of the slope predicted by zero-thickness e at plate theory.
Abstract: Numerical simulations of leading-edge acoustic receptivity are performed for a e at plate with a modie ed-superelliptic leading edge. For small freestream amplitude the agreement between branch I receptivity coefe cients predicted from the direct numerical simulation (DNS) and the experiments for acoustic waves at zero incidence is excellent. The effect of angle of incidence of the impinging wave is investigated and found to produce higher receptivity coefe cients than in the symmetric case. The slope of leading-edge receptivity coefe cient vs angle of incidence of the impinging wave is found to be less than 1 of the slope predicted by zero-thickness e at-plate theory. However, there is excellent agreement between theDNS and e nite-nose-radius theory. These resultsclearly demonstrate the importance of including the effects of the e nite nose radius in any receptivity study. Finally, downstream of the leading-edge region linear stability theory is found to reproduce accurately the characteristics of the instability waves. At higher freestream forcing, an instability wave generated by nonlinear interaction is found at double the frequency of the forcing.

25 citations

Journal ArticleDOI
TL;DR: In this paper, an improved numerical algorithm that solves the full mean compressible Navier-Stokes equations has been applied to the calculation of the flowfield in three separate configurations of a simulated high speed aircraft inlet.
Abstract: An improved numerical algorithm that solves the full mean compressible Navier-Stokes equations has been applied to the calculation of the flowfield in three separate configurations of a simulated high speed aircraft inlet. The inlet geometry consists of a converging supersonic diffuser, formed by two nonparallel plates, followed by a constant height "throat." For all cases, the freestream Mach number is 3.51, and the Reynolds number is 13.6 X10 based on the inlet length. The three configurations are characterized by different values of the angle of the converging supersonic diffuser and different boundary-layer bleed schedules. The computed results are compared with detailed experimental data for the ramp and cowl surface pressure distribution, and the boundary-layer pitot profiles at seven different streamwise locations. The agreement with the experimental results is generally good, although the experimental data display evidence of three dimensionality over a portion of the inlet flowfield.

25 citations

Proceedings ArticleDOI
Andrew C. Nix1, A. C. Smith1, Thomas E. Diller1, Wing Ng1, Karen A. Thole1 
01 Jan 2002
TL;DR: In this article, the authors developed a turbulence grid capable of generating high intensity, large-scale turbulence for use in experimental heat transfer measurements in a transonic facility, which is desired to produce freestream turbulence characteristic of the flow exiting the combustor of advanced gas turbine engines.
Abstract: Heat transfer predictions in gas turbine engines have focused on cooling techniques and on the effects of various flow phenomena. The effects of wakes, passing shock waves and freestream turbulence have all been of primary interest to researchers. The focus of the work presented in this paper is to develop a turbulence grid capable of generating high intensity, large-scale turbulence for use in experimental heat transfer measurements in a transonic facility. The grid is desired to produce freestream turbulence characteristic of the flow exiting the combustor of advanced gas turbine engines. A number of techniques are discussed in this paper to generate high intensity, large length-scale turbulence for a transonic facility. Ultimately, the passive grid design chosen is capable of producing freestream turbulence with intensity of approximately 10–12% near the entrance of the cascade passages with an integral length-scale of 2 cm.Copyright © 2002 by ASME

25 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
2023195
2022350
2021108
2020113
201986
2018118