A Method of Solving Supersonic Laminar Boundary-Layer Separation and Its Application to Wedges and Curved SurfacesSource: Journal of Applied Mechanics:;1965:;volume( 032 ):;issue: 004::page 747Author:Oscar Pinkus
DOI: 10.1115/1.3627312Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: By use of a quartic velocity profile with one of its coefficients varying along the boundary layer, a technique is developed to calculate the general characteristics of adiabatic separated flows. The technique is based on the integral solution of the differential equations of laminar compressible boundary layers utilizing the energy-momentum concept and on expressions derived from the notion of a dividing streamline in the separated region. Detaching, central, and reattaching regions are defined which, by their combination, embrace most known forms of flow separation. The derived equations are here applied to the case of separated laminar boundary layers on compression corners and curved surfaces.
keyword(s): Separation (Technology) , Boundary layers , Wedges , Differential equations , Compression , Equations , Flow separation , Corners (Structural elements) , Momentum AND Flow (Dynamics) ,
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| contributor author | Oscar Pinkus | |
| date accessioned | 2017-05-08T23:25:37Z | |
| date available | 2017-05-08T23:25:37Z | |
| date copyright | December, 1965 | |
| date issued | 1965 | |
| identifier issn | 0021-8936 | |
| identifier other | JAMCAV-25817#747_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/102979 | |
| description abstract | By use of a quartic velocity profile with one of its coefficients varying along the boundary layer, a technique is developed to calculate the general characteristics of adiabatic separated flows. The technique is based on the integral solution of the differential equations of laminar compressible boundary layers utilizing the energy-momentum concept and on expressions derived from the notion of a dividing streamline in the separated region. Detaching, central, and reattaching regions are defined which, by their combination, embrace most known forms of flow separation. The derived equations are here applied to the case of separated laminar boundary layers on compression corners and curved surfaces. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | A Method of Solving Supersonic Laminar Boundary-Layer Separation and Its Application to Wedges and Curved Surfaces | |
| type | Journal Paper | |
| journal volume | 32 | |
| journal issue | 4 | |
| journal title | Journal of Applied Mechanics | |
| identifier doi | 10.1115/1.3627312 | |
| journal fristpage | 747 | |
| journal lastpage | 756 | |
| identifier eissn | 1528-9036 | |
| keywords | Separation (Technology) | |
| keywords | Boundary layers | |
| keywords | Wedges | |
| keywords | Differential equations | |
| keywords | Compression | |
| keywords | Equations | |
| keywords | Flow separation | |
| keywords | Corners (Structural elements) | |
| keywords | Momentum AND Flow (Dynamics) | |
| tree | Journal of Applied Mechanics:;1965:;volume( 032 ):;issue: 004 | |
| contenttype | Fulltext |