Measurements of the Surface Pressure Fluctuations in a Turbulent Boundary Layer in Air at Supersonic Speeds PDF Download
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Author: D.J.M. Williams
Publisher:
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Category :
Languages : en
Pages :
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Author: D.J.M. Williams
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Category :
Languages : en
Pages :
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Author: Kizhanatham Raghavachary Raman
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 100
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Author: Alan L. Kistler
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
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Measurements were obtained of the pressure fluctuations on a solid surface immersed in a supersonic stream for Mach numbers up to 5.0. The pressures resulting from both the attached and separated turbulent boundary layers were investigated. The results for the attached layer show that the root mean square value of the pressure fluctuation is proportional to the mean shear stress at the wall with a proportionality constant that is only weakly dependent on Mach number. The convection velocity characterizing the space-time correlations of pressure on the wall decreases with increasing Mach number, as does the ratio of the scale of the pressure fluctuations to the geometrical boundary layer thickness. The pressures associated with the separated flow produced by a forward facing step were significantly larger than the pressures produced by an attached boundary layer. The data can be interpreted as showing that the pressure fluctuations originate from two distinct causes, fluctuations due to changes in geometry of the separated region and fluctuations due to the disturbed motion within the separation bubble. (Author).
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: Walter J. Trapp
Publisher:
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Category : Airplanes
Languages : en
Pages : 506
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Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Author: William A. Cassels
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
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Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author: United States. National Aeronautics and Space Administration
Publisher:
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Category : Astronautics
Languages : en
Pages : 756
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Author:
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Category :
Languages : en
Pages : 538
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 566
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