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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 article, the effects of heat transfer on turbulent shear stresses in a Mach 3 compressible boundary layer were investigated by an x-probe in a flat plate, zero pressure gradient, two dimensional boundary layer in a wind tunnel with wall to freestream temperature ratios of 0.94 and 0.71.
Abstract: Hot-wire anemometer measurements of turbulent shear stresses in a Mach 3 compressible boundary layer were performed in order to investigate the effects of heat transfer on turbulence. Measurements were obtained by an x-probe in a flat plate, zero pressure gradient, two dimensional boundary layer in a wind tunnel with wall to freestream temperature ratios of 0.94 and 0.71. The measured shear stress distributions are found to be in good agreement with previous results, supporting the contention that the shear stress distribution is essentially independent of Mach number and heat transfer for Mach numbers from incompressible to hypersonic and wall to freestream temperature ratios of 0.4 to 1.0. It is also found that corrections for frequency response limitations of the electronic equipment are necessary to determine the correct shear stress distribution, particularly at the walls.

22 citations

Journal ArticleDOI
01 May 2008
TL;DR: In this article, the interaction of the laser-induced plasma produced by a pulse laser energy deposition with the shock wave over a blunt body in a freestream Mach number of 3 was studied numerically and exp...
Abstract: The interaction of the laser-induced plasma produced by a pulse laser energy deposition with the shock wave over a blunt body in a freestream Mach number of 3 is studied numerically and exp...

22 citations

Proceedings ArticleDOI
01 Jan 1990
TL;DR: In this article, a joint experimental and computational study of skin friction in weak-to-strong swept shock wave/turbulent boundary-layer interactions has been carried out, and the results show a systematic rise in the peak c(f) at the rear part of the interaction, where the separated flow atttaches.
Abstract: A joint experimental and computational study of skin friction in weak-to-strong swept shock wave/turbulent boundary-layer interactions has been carried out. A planar shock wave is generated by a sharp fin at angles of attack alpha = 10 deg and 16 deg at M(infinity) = 3 and 16 and 20 deg at M(infinity) = 4. Measurements are made using the Laser Interferometer Skin Friction meter, which optically detects the rate of thinning of an oil film applied to the test surface. The results show a systematic rise in the peak c(f) at the rear part of the interaction, where the separated flow atttaches. For the stronget case studied, this peak is an order of magnitude higher than the incoming freestream c(f)level.

22 citations

Journal ArticleDOI
TL;DR: In this paper, the authors investigated the characteristics of surface pressures over bluff bodies in separated and reattaching flows, with emphasis placed on the effects of freestream turbulence and leading edge geometry.

22 citations

Journal ArticleDOI
TL;DR: In this paper, the combined influences of low Reynolds number effects and the high levels of freestream turbulence, present within the atmospheric boundary layer, make it difficult to control/fly outdoors.
Abstract: Micro air vehicles are typically small in size and are remotely controlled or autonomous aircraft that fly slowly (50; 000 < Reynolds number < 200; 000) and very close to the Earth's surface. Due to the combined influences of low Reynolds number effects and the high levels of freestream turbulence, present within the atmospheric boundary layer, micro air vehicles are very difficult to control/fly outdoors.

22 citations


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