Author: Martin Hugh Rogers (CAPT, USAF.)Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages :
Book Description
A Numerical Investigation of Pressure Gradient Effects on Supersonic Turbulent Flow
Author: Martin Hugh Rogers (CAPT, USAF.)Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages :
Book Description
A Numerical Investigation of Supersonic Turbulent Shear Layers
Author: Choong K. OhTurbulent 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 and Numerical Investigation of Supersonic Turbulent Flow in an Annular Duct
Author: K. E. WilliamsPressure Gradient Effects on Supersonic Boundary Layer Turbulence
Author: A. J. LadermanPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 182
Book Description
Measurements of mean flow profiles at several streamwise locations in a supersonic turbulent boundary layer growing under a continuous adverse pressure gradient are reported. Tests were performed at a freestream Mach number of 3, for an adiabatic wall, using two curved ramps designed to produce constant pressure gradient flows. The velocity profile data, when transformed to incompressible coordinates, are in good agreement with Coles universal 'wall-wake' velocity profile and they indicate that the boundary layer is in local equilibrium and essentially independent of upstream history. In addition, the Coles wake parameters and Clauser shape factors, characterizing the transformed profiles, are in accord with the results of low speed correlations of adverse pressure gradient flows. The turbulent transport terms were extracted from the mean flow field data and indicate that for a given ramp, the profile of turbulent shear stress normalized by the wall shear, versus distance from the surface, normalized by the local boundary thickness, is severely distored by the pressure gradient although it is apparently insensitive to local conditions.
Numerical Simulation of Supersonic Turbulent Boundary Layer Flow with Mild Pressure Gradient
Author: E. T. FickInvestigation of Supersonic Turbulent Boundary-layer Separation on a Compression Ramp by an Integral Method
Author: Numerical Investigation of Supersonic Turbulent Boundary Layers
Author: Thierry MaederPublisher:
ISBN: 9783183394074
Category :
Languages : en
Pages : 119
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).
Numerical Simulation of Supersonic Turbulent Boundary Layer Flow Under the Influence of Mild Pressure Gradients
Author: Eric Thomas FickPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 276
Book Description