Calculation Of Laminar Separation With Free Interaction By The Method Of Integral Relations PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Calculation Of Laminar Separation With Free Interaction By The Method Of Integral Relations PDF full book. Access full book title Calculation Of Laminar Separation With Free Interaction By The Method Of Integral Relations.
Author | : Jack Norman Nielsen |
Publisher | : |
Total Pages | : 92 |
Release | : 1966 |
Genre | : Aerodynamic heating |
ISBN | : |
Download Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations Book in PDF, ePub and Kindle
"A calculative method is presented for determining separated, laminar, boundary-layer characteristics from in front of the separation point to the reattachment point under the influence of 'free interaction' between the main flow and the boundary layer. The analysis covers supersonic flow over two-dimensional and axisymmetric configurations with adiabatic or nonadiabatic wall conditions. For nonadiabatic wall conditions, theories based on first-order coupling and second-order coupling between velocity and total temperature profiles were presented. The theory based on first-order coupling was included in a machine calculation program with options for two-dimensional or axisymmetric flow and adiabatic or nonadiabatic wall conditions. Extensive systematic calculations were made to determine the range of possible separated flows over a two-dimensional configuration as a function of separation point location and wall temperatures. Comparison between experiment and theory for separation pressure distributions on two-dimensional or axisymmetric adiabatic configurations shows generally good agreement. Good comparison between experiment and theory is indicated for a moderately-cooled axisymmetric configuration. For a highly-cooled axisymmetric configuration, the prediction of the machine program based on first-order coupling is inadequate, indicating the necessity for a higher-order coupling theory." -- page iii.
Author | : Jack N. Nielsen |
Publisher | : |
Total Pages | : 121 |
Release | : 1965 |
Genre | : |
ISBN | : |
Download Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations. Part I. Two-dimensional Supersonic Adiabatic Flow Book in PDF, ePub and Kindle
Methods are presented for calculating the laminar boundary-layer flow through separation to reattachment under the influence of a prescribed pressure gradient or, in the case of a supersonic main stream, under the influence of 'free interaction' between the boundary layer and the main flow. The present method is based on the Dorodnitsyn method of integral relations and uses a rational velocccity profile which accounts properly for the separation singularity. As a result, the possibility of higher approximations is inherent in the method. The calculated solution for free interaction goes smoothly through the separation point and is in good agreement with certain features of the Navier-Stokes solution in the neighborhood of separation. Good agreement is exhibited between experimental and calculated pressure distributions up to reattachment for the several cases for which the comparisons were made. A computer program based on the work was prepared for two-dimensional flow. It is planned to continue the work to cover nonadiabatic boundary layers and axisymmetric bodies. (Author).
Author | : Jack N. Nielsen |
Publisher | : |
Total Pages | : |
Release | : 1965 |
Genre | : |
ISBN | : |
Download Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations. Pt. 1. Two-dimensional Supersonic Adiabatic Flow Book in PDF, ePub and Kindle
Author | : Jack N. Nielsen |
Publisher | : |
Total Pages | : 103 |
Release | : 1965 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations Book in PDF, ePub and Kindle
Methods are presented for calculating the laminar boundary-layer flow through separation to reattachment under the influence of a prescribed pressure gradient or, in the case of a supersonic main stream, under the influence of 'free interaction' between the boundary layer and the main flow. The present method is based on the Dorodnitsyn method of integral relations and uses a rational velocccity profile which accounts properly for the separation singularity. As a result, the possibility of higher approximations is inherent in the method. The calculated solution for free interaction goes smoothly through the separation point and is in good agreement with certain features of the Navier-Stokes solution in the neighborhood of separation. Good agreement is exhibited between experimental and calculated pressure distributions up to reattachment for the several cases for which the comparisons were made. A computer program based on the work was prepared for two-dimensional flow. It is planned to continue the work to cover nonadiabatic boundary layers and axisymmetric bodies. (Author).
Author | : Jack N. Nielsen |
Publisher | : |
Total Pages | : |
Release | : 1966 |
Genre | : |
ISBN | : |
Download Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations. Pt. 2. Two-dimensional Supersonic Nonadiabatic Flow and Axisymmetric Supersonic Adiabatic and Nonadiabatic Flows Book in PDF, ePub and Kindle
Author | : Jack N. NIELSEN |
Publisher | : |
Total Pages | : 91 |
Release | : 1966 |
Genre | : |
ISBN | : |
Download Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations. Part Ii. Two-dimensional Supersonic Nonadiabatic Flow and Axisymmetric Supersonic Adiabatic and Nonadiabatic Flows Book in PDF, ePub and Kindle
A alculative method is presented for determining separated, laminar, boundary-layer characteristics from in front of the separation point to the reattachment point under the influence of 'free interaction' between the main flow and the boundary layer. The analysis covers supersonic flow over two-dimensional and axisymmetric configurations with adiabatic or nonadiabatic wall conditions. For nonadiabatic wall conditions, theories based on first-order coupling and second-order coupling between velocity and total temperature profiles were presented. The theory based on first-order coupling was included in a machine calculation program with options for two-dimensional or axisymmetric flow and adiabatic or nonadiabatic wall conditions. Extensive systematic calculations were made to determine the range of possible separated flows over a two-dimensional configuration as a function of separation point location and wall temperatures. Comparison between experiment and theory for separation pressure distributions on two -dimensional or axisymmetric adiabatic configurations shows generally good agreement. (Author).
Author | : |
Publisher | : |
Total Pages | : 892 |
Release | : 1974 |
Genre | : Aeronautics |
ISBN | : |
Download NASA Technical Note Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 580 |
Release | : 1969 |
Genre | : Compressibility |
ISBN | : |
Download Compressible Turbulent Boundary Layers Book in PDF, ePub and Kindle
Author | : John D. Murphy |
Publisher | : |
Total Pages | : 36 |
Release | : 1971 |
Genre | : Boundary layer |
ISBN | : |
Download A Critical Evaluation of Analytic Methods for Predicting Laminar Boundary-layer, Shock-wave Interaction Book in PDF, ePub and Kindle
Author | : Frederick K. Goodwin |
Publisher | : |
Total Pages | : 60 |
Release | : 1969 |
Genre | : Axial flow |
ISBN | : |
Download Inhibition of Flow Separation at High Speed Book in PDF, ePub and Kindle
This is the last part of a four-part series of reports describing an investigation of the inhibition of boundary-layer separation of the free-interaction type at high speeds through the use of surface cooling. The purpose of this report is to extend the other work of the authors to configurations representative of axisymmetric compression spikes. The analysis is developed and a computer program written for a spike which consists of a conical nose on which separation occurs followed by compression surface. No data were found to compare with the theory. A calculation made with the pressure gradient prescribed by the body shape rather than by free interaction is compared with experiment. The comparisons, which were made for skin friction, heat transfer, and pressure distributions, were good. The significant effect of wall cooling in delaying separation for the prescribed pressure gradient case is shown. It is also shown that a free-interaction solution can be joined to a prescribed pressure gradient solution so that the solution will go smoothly through separation to reattachment.