On the Wall-Normal Velocity of the Compressible Boundary-Layer Equations

On the Wall-Normal Velocity of the Compressible Boundary-Layer Equations PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722458843
Category :
Languages : en
Pages : 46

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Book Description
Numerical methods for the compressible boundary-layer equations are facilitated by transformation from the physical (x, y) plane to a computational (xi, eta) plane in which the evolution of the flow is 'slow' in the time-like xi direction. The commonly used Levy-Lees transformation results in a computationally well-behaved problem for a wide class of non-similar boundary-layer flows, but it complicates interpretation of the solution in physical space. Specifically, the transformation is inherently nonlinear, and the physical wall-normal velocity is transformed out of the problem and is not readily recovered. In light of recent research which shows mean-flow non-parallelism to significantly influence the stability of high-speed compressible flows, the contribution of the wall-normal velocity in the analysis of stability should not be routinely neglected. Conventional methods extract the wall-normal velocity in physical space from the continuity equation, using finite-difference techniques and interpolation procedures. The present spectrally-accurate method extracts the wall-normal velocity directly from the transformation itself, without interpolation, leaving the continuity equation free as a check on the quality of the solution. The present method for recovering wall-normal velocity, when used in conjunction with a highly-accurate spectral collocation method for solving the compressible boundary-layer equations, results in a discrete solution which is extraordinarily smooth and accurate, and which satisfies the continuity equation nearly to machine precision. These qualities make the method well suited to the computation of the non-parallel mean flows needed by spatial direct numerical simulations (DNS) and parabolized stability equation (PSE) approaches to the analysis of stability. Pruett, C. David Unspecified Center NAS1-18599; RTOP 505-59-53-02.

On the Wall-Normal Velocity of the Compressible Boundary-Layer Equations

On the Wall-Normal Velocity of the Compressible Boundary-Layer Equations PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722458843
Category :
Languages : en
Pages : 46

Get Book Here

Book Description
Numerical methods for the compressible boundary-layer equations are facilitated by transformation from the physical (x, y) plane to a computational (xi, eta) plane in which the evolution of the flow is 'slow' in the time-like xi direction. The commonly used Levy-Lees transformation results in a computationally well-behaved problem for a wide class of non-similar boundary-layer flows, but it complicates interpretation of the solution in physical space. Specifically, the transformation is inherently nonlinear, and the physical wall-normal velocity is transformed out of the problem and is not readily recovered. In light of recent research which shows mean-flow non-parallelism to significantly influence the stability of high-speed compressible flows, the contribution of the wall-normal velocity in the analysis of stability should not be routinely neglected. Conventional methods extract the wall-normal velocity in physical space from the continuity equation, using finite-difference techniques and interpolation procedures. The present spectrally-accurate method extracts the wall-normal velocity directly from the transformation itself, without interpolation, leaving the continuity equation free as a check on the quality of the solution. The present method for recovering wall-normal velocity, when used in conjunction with a highly-accurate spectral collocation method for solving the compressible boundary-layer equations, results in a discrete solution which is extraordinarily smooth and accurate, and which satisfies the continuity equation nearly to machine precision. These qualities make the method well suited to the computation of the non-parallel mean flows needed by spatial direct numerical simulations (DNS) and parabolized stability equation (PSE) approaches to the analysis of stability. Pruett, C. David Unspecified Center NAS1-18599; RTOP 505-59-53-02.

On the Wall-normal Velocity of the Compressible Boundary-layer Equations

On the Wall-normal Velocity of the Compressible Boundary-layer Equations PDF Author: Charles David Pruett
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 50

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Book Description


On the Wall-normal Velocity of the Compressible Boundary-layer Equations

On the Wall-normal Velocity of the Compressible Boundary-layer Equations PDF Author: C. David Pruett
Publisher:
ISBN:
Category :
Languages : en
Pages : 48

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Book Description


On the Wall-normal Velocity of the Compressible Boundary-layer Equations

On the Wall-normal Velocity of the Compressible Boundary-layer Equations PDF Author: Charles David Pruett
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 48

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Book Description


Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data

Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data PDF Author: Julius E. Harris
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 92

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Book Description
A numerical method for solving the equations for laminar, transitional, and turbulent compressible boundary layers for either planar or axisymmetric flows is presented. The fully developed turbulent region is treated by replacing the Reynolds stress terms with an eddy viscosity model. The mean properties of the transitional boundary layer are calculated by multiplying the eddy viscosity by an intermittency function based on the statistical production and growth of the turbulent spots. A specifiable turbulent Prandtl number relates the turbulent flux of heat to the eddy viscosity. A three-point implicit finite-difference scheme is used to solve the system of equations. The momentum and energy equations are solved simultaneously without iteration. Numerous test cases are compared with experimental data for supersonic and hypersonic flows; these cases include flows with both favorable and mildly unfavorable pressure gradient histories, mass flux at the wall, and traverse curvature.

Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients

Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients PDF Author: Shimer Zane Pinckney
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68

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Book Description


Boundary-Layer Theory

Boundary-Layer Theory PDF Author: Hermann Schlichting (Deceased)
Publisher: Springer
ISBN: 366252919X
Category : Technology & Engineering
Languages : en
Pages : 814

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Book Description
This new edition of the near-legendary textbook by Schlichting and revised by Gersten presents a comprehensive overview of boundary-layer theory and its application to all areas of fluid mechanics, with particular emphasis on the flow past bodies (e.g. aircraft aerodynamics). The new edition features an updated reference list and over 100 additional changes throughout the book, reflecting the latest advances on the subject.

Stability of Three-dimensional Compressible Boundary Layers

Stability of Three-dimensional Compressible Boundary Layers PDF Author: Eli Reshotko
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48

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Book Description


Similar Solutions for the Compressible Boundary Layer on a Yawed Cylinder with Transpiration Cooling

Similar Solutions for the Compressible Boundary Layer on a Yawed Cylinder with Transpiration Cooling PDF Author: Ivan E. Beckwith
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 44

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Book Description
Heat-transfer and skin-friction parameters obtained from exact solutions to the laminar compressible boundary-layer equations for infinite cylinders in yaw are presented. The effects of transpiration cooling, Prandtl number, pressure gradient, wall temperature, and viscosity relation were investigated. It is shown that as the Mach number is increased for a given large yaw angle the effects of pressure gradient become larger and the quantity of coolant required to maintain a given wall temperature is also increased. The use of a linear viscosity-temperature relation gives approximately the same results as the Sutherland viscosity-temperature relation except for very high aerodynamic heating rates.

The Laminar Boundary Layer Equations

The Laminar Boundary Layer Equations PDF Author: N. Curle
Publisher: Courier Dover Publications
ISBN: 0486812391
Category : Science
Languages : en
Pages : 177

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Book Description
Thorough introduction to boundary layer problems offers an ordered, logical presentation accessible to undergraduates. The text's careful expositions of the limitations and accuracy of various methods will also benefit professionals. 1962 edition.