Author: Alfred WalzPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 28
Book Description
Compressible Turbulent Boundary Layers with Heat Transfer and Pressure Gradient in Flow Direction
Author: Alfred WalzPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 28
Book Description
An Experimental Investigation of the Compressible Turbulent Boundary Layer with a Favorable Pressure Gradient
Author: David L. BrottPublisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 104
Book Description
The paper describes the results of a detailed experimental investigation of a two-dimensional turbulent boundary layer in a favorable pressure gradient where the free-stream Mach number varied from 3.8 to 4.6 and the ratio of wall to adiabatic-wall temperature has a nominal value of 0.82. Detailed profile measurements were made with pressure and temperature probes; skin friction was measured directly with a shear balance. The velocity- and temperature-profile results were compared with zero pressure gradient and incompressible results. The skin-friction data were correlated with momentum-thickness Reynolds number and pressure-gradient parameter. (Author).
Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients
Author: Shimer Zane PinckneyPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 68
Book Description
An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient: The Compressibility transformation
Author: Constantino EconomosPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 52
Book Description
This report investigates the behavior of high speed turbulent boundary layer with heat transfer and streamwise pressure gradient.
Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data
Author: Julius E. HarrisPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 92
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.
Calculation of Turbulent Boundary Layers with Heat Transfer and Pressure Gradient Utilizing a Compressibility Transformation
Author: J. SchneiderPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 106
Book Description
A computer program is described capable of determining the properties of a compressible turbulent boundary layer with pressure gradient and heat transfer. The program treats the two-dimensional problem assuming perfect gas and Crocco integral energy solution. A compressibility transformation is applied to the equation for the conservation of mass and momentum, which relates this flow to a low speed constant property flow with simultaneous mass transfer and pressure gradient. The resulting system of describing equations consists of eight ordinary differential equations which are solved numerically. For Part 1, see N72-12226; for Part 2, see N72-15264.
An Investigation of the High Speed Turbulent Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient. Part 2 - The Compressibility Transformation - General Considerations
Author: Calculation of Turbulent Boundary Layers with Heat Transfer and Pressure Gradient Utilizing a Compressibility Transformation. Part 2: Constant Property Turbulent Boundary Layer Flow with Simultaneous Mass Transfer and Pressure Gradient
Author: Compressible Turbulent Boundary Layer with Arbitrary Pressure Gradient and Heat Transfer
Author: Philip K. SasmanPublisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 36
Book Description
The compressible turbulent boundary layer is expressed in terms of the momentum integral and moment of momentum integral equations for arbitrary pressure gradient. Upon simplification of this equation set with a Mager type transformation, the two coupled differential equations are solved simulataneously to provide boundary layer momentum thickness, displacement thickness, skin friction coefficient and related quantities as a function of the body surface coordinate. The analysis includes surface heat-transfer effects. Results of the analysis are presented for adiabatic, non-adiabatic, twodimensional and axisymmetric flow fields in a Mach number range between 2 and 8. Flows with adverse pressure gradients are also examined. The present analysis is compared with available experimental and theoretical results. The analysis is found to yield satisfactory results for flows with and without heat transfer. In addition, for flows in the presence of large adverse pressure gradients in which the boundary layer is known to be well-behaved, spurious separation is not indicated; instead, rather good agreement with available experimental data is observed. (Author).
Calculation of Compressible Turbulent Boundary Layers with Pressure Gradients and Heat Transfer
Author: Larry L. LynesPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 146
Book Description