![Charts and Tables for Estimating Stability of Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient [with List of References] PDF](https://books.google.com/books/content/images/frontcover/MHnqZwEACAAJ?fife=w150-h200)
Author: Publisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 48
Book Description
Charts and Tables for Estimating Stability of Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient [with List of References]
![Charts and Tables for Estimating Stability of Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient [with List of References] PDF](https://books.google.com/books/content/images/frontcover/MHnqZwEACAAJ?fife=w80-h100)
Author: Publisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 48
Book Description
Monthly Catalog of United States Government Publications
Author: United States. Superintendent of DocumentsPublisher:
ISBN:
Category : Government publications
Languages : en
Pages : 2106
Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
The Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient
Author: Clarence B. CohenPublisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 43
Book Description
WIth the resulting relations, methods are derived for the calculation of the tw-dimensional and axially symmetric laminar boundary layer with an arbitrary free-stream velocity distribution, Mach number, and surface temperature.
The Upper-branch Stability of Compressible Boundary Layer Flows
Author: J. S. B. GajjarThe Compressible Laminar Boundary Layer with Heat Transfer and Arbitary Pressure Gradient
Author: Clarence B. CohenSimilar Solutions for the Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient
Author: Clarence B. CohenPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 67
Book Description
Stewartson's transformation is applied to the laminar compressible boundary-layer equations and the requirement of similarity is introduced, resulting in a set of ordinary nonlinear differential equations previously quoted by Stewartson, but unsolved. The requirements of the system are Prandtl number of 1.0, linear viscosity-temperature relation across the boundary layer, an isothermal surface, and the particular distributions of free-stream velocity consistent with similar solutions. This system admits axial pressure gradients of arbitrary magnitude, heat flux normal to the surface, and arbitrary Mach numbers. The system of differential equations is transformed to integral system, with the velocity ratio as the independent variable. For this system, solutions are found by digital computation for pressure gradients varying from that causing separation to the infinitely favorable gradient and for wall temperatures from absolute zero to twice the free-stream stagnation temperature. Some solutions for separated flows are also presented.
Method for Calculation of Compressible Laminar Boundary Layer with Pressure Gradient and Heat Transfer
Author: Paul A. LibbyMethod for Calculation of Compressible Laminar Boundary-layer Characteristics in Axial Pressure Gradient with Zero Heat Transfer
Author: Morris MorduchowPublisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 43
Book Description
The Karman-Pohlhausen method is extended primarily to sixth-degree velocity profiles for determining the characteristics of the compressible laminar boundary layer over an adiabatic wall in the presence of an axial pressure gradient. It is assumed that the Prandtl number is unity and that the coefficient of viscosity varies linearly with the temperature. A general approximate solution which permits a rapid determination of the boundary layer characteristics for any given free-stream Mach number and given velocity distribution at the outer edge of the boundary layer is obtained. Numerical examples indicated that this solution will practice lead to results of satisfactory accuracy, including the critical Reynolds number for stability. For the special purpose of calculating the location of the separation point in an adverse pressure gradient, a short and simple method, based on the use of a seventh-degree velocity profile, is derived. The numerical example given here indicates that this method should in practice lead to sufficiently accurate results. For the special case of flow near a forward stagnation point it is shown that the Karman-Pohlhausen method with the usual fourth-degree profiles leads to results of adequate accuracy, even for the critical Reynolds number.
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.
Exact Solutions of Laminar-boundary-layer Equations with Constant Property Values for Porous Wall with Variable Temperature
Author: Patrick L. DonoughePublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 50
Book Description
Exact solutions of the laminar-boundary-layer equations for wedge-type flow with constant property values are presented for transpiration-cooled surfaces with variable wall temperatures. The difference between wall and stream temperature is aussumed proportional to a power of the distance from the leading edge. Solutions are given for a Prandtl number of 0.7 and ranges of pressure-gradient, cooling-air-flow, and wall-temperature-gradient parameters. Boundary-layer profiles, dimensionaless boundary-layer thicknesses, and heat-transfer coefficents are given in both tabular and graphical form. Corresponding results for constant wall temperature and for impermeable surfaces are included for comparison purposes.