Author: D.J.M. WilliamsPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Measurements of the Surface Pressure Fluctuations in a Turbulent Boundary Layer in Air at Supersonic Speeds
Author: D.J.M. WilliamsA Study of Surface Pressure Fluctuations in Hypersonic Turbulent Boundary Layers
Author: Kizhanatham Raghavachary RamanPublisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 100
Book Description
NASA Technical Note
Author: Scientific and Technical Aerospace Reports
Author: Surface Pressure Fluctuations Produced by Attached and Separated Supersonic Boundary Layers
Author: Alan L. KistlerPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
Book Description
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).
Turbulent Shear Layers in Supersonic Flow
Author: Alexander J. SmitsPublisher: Springer Science & Business Media
ISBN: 0387263055
Category : Science
Languages : en
Pages : 418
Book Description
A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
Power- and Cross-spectra and Space-time Correlations of Surface Fluctuating Pressures at Mach Numbers Between 1.6 and 2.5
Author: Wei J. ChyuPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
WADC-University of Minnesota Conference on Acoustical Fatigue
Author: Walter J. TrappPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 506
Book Description
Basic Aerodynamic Noise Research
Author: Ira R. SchwartzPublisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 548
Book Description
Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds
Author: William A. CasselsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
Book Description
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.