Author: V. M. KovalenkoPublisher:
ISBN:
Category :
Languages : en
Pages : 12
Book Description
Experimental Investigation of a Turbulent Boundary Layer on a Greatly Elongated Body of Revolution in a Supersonic Flow
Author: V. M. KovalenkoExperimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds
Author: William R. WimbrowPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
Book Description
Local temperature recovery factors have been measured on two bodies of revolution at Mach numbers of 2.0 and are shown to be independent of Mach number, Reynolds number, or body shape. The measured recovery factor is well represented by the square root of Prandtl number for laminar boundary layers and by the cube root of Prandtl number for turbulent boundary layers, as predicted by theory.
Scientific and Technical Aerospace Reports
Author: 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.
A Method for Determining the Total Drag of a Pointed Body of Revolution in Supersonic Flow with Turbulent Boundary Layer
Author: Charlie M. JacksonPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 74
Book Description
An Experimental Investigation of the Turbulent Boundary Layer in Supersonic Airflow
Author: Henk AltmannPublisher:
ISBN:
Category : Engineering
Languages : en
Pages :
Book Description
An Experimental Investigation of the Supersonic Turbulent Boundary Layer in a Moderate Adverse Pressure Gradient. Part II. Analysis of the Experimental Data
Author: W. B. SturekPublisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The experimental data reported in Part 1 are analyzed. Turbulent boundary layer equations applicable to compressible flow over a surface with longitudinal curvature are evaluated by numerical integration using the tabulated profile data. Curvature corrections to the equation for conservation of streamwise momentum are shown to be small but of the same order of magnitude as the wall shear stress. The data are shown to correlate in law of the wall and velocity defect dimensionless coordinates using an integral compressibility transformation. Values of skin friction coefficient calculated using the experimental data are compared to other experimental data and to values predicted using the Spalding-Chi method. (Author).
Turbulent-boundary-layer Characteristics of Pointed Slender Bodies of Revolution at Supersonic Speeds
Author: Jerry M. AllenTurbulent 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.
Experimental Investigation of the Pressure Rise Required for the Incipient Separation of Turbulent Boundary Layers in Two-dimensional Supersonic Flow
Author: Donald M. KuehnPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description