Download or read book Turbulent Boundary layer Separation Induced by Flares on Cylinders at Zero Angle of Attack with List of References written by and published by . This book was released on 1962 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Turbulent Boundary layer Separation Induced by Flares on Cylinders at Zero Angle of Attack written by Donald M. Kuehn and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Separation caused by the pressure rise induced by flares has been experimentally investigated in the Mach number range of 1.5 to 5.0 and in the Reynolds number range (based on boundary-layer thickness) of 1.5X104 to 12X104. The purpose of the investigation was to determine the model geometry and flow conditions for which separation can be expected for a turbulent boundary layer of zero pressure gradient on the cylinder approaching the flare. Comparisons are made of the boundary-layer-separation characteristics of these three-dimensional flares with two-dimensional separation results from a previous investigation.

Download or read book Turbulent Boundary layer Separation Induced by Flares on Cylinders at Zero Angle of Attack written by Donald M. Kuehn and published by . This book was released on 1961 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Boundary layer Separation Induced by Flares on Cylinders with Highly Cooled Boundary Layers at a Mach Number of 15 written by Donald M. Kuehn and published by . This book was released on 1965 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 1962 with total page 1990 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Boundary layer Separation Induced by Flares on Cylinders with Highly Cooled Boundary Layers at a Mach Number of 15 written by Donald M. Kuehn and published by . This book was released on 1965 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experiments on Turbulent Bounday Layers Along a Circular Cylinder with and Without Separation written by Hans Fernholz and published by . This book was released on 1967 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of Turbulent Step induced Boundary layer Separation at Mach Numbers 2 5 3 and 4 written by Jerry S. Hahn and published by . This book was released on 1969 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of turbulent separated boundary-layer flow was conducted using high forward-facing steps (with side plates) mounted on a flat plate at zero angle of attack. The tests were made at Mach numbers of 2.5, 3.0, and 4.0 for Reynolds numbers, based on the boundary-layer total thickness at the separation location, from 100,000 to 150,000. The effects of Mach number, step height and span, end plates, and step-face fairings were investigated. Data are presented graphically and in tabulations and include model surface pressures on the flat plate and on the face and top of selected steps, boundary-layer Mach number profiles, and selected oil dot photographs. (Author).

Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1962 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1962 with total page 1164 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book On Separating Turbulent Boundary Layers written by W. H. Schofield and published by . This book was released on 1983 with total page 8 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some data and theories of two dimensional turbulent boundary layer separation are considered. A description of separating layers based on the Schofield and Perry similarity is proposed. It is shown that the Schofield and Perry defect law can describe detached profiles as accurately as it can describe attached profiles if the origin is shifted, from the wall, out to the zero velocity position in the detached flow. For an attached flow the inner wall matching condition is the usual law of the wall. For detached flow the wall matching condition is provided by the reversed flow for which a modified similarity scale is proposed. This extended validity of the Schofield and Perry defect law implies a unique progression of mean velocity profile shapes up to and through separation. Good experimental support for this theoretical result is presented. Experimental evidence also supports the proposition that detachment (and perhaps reattachment) always occurs at the same position on the locus of profile shapes, that is, boundary layers detach with a universal mean profile shape. A comparison of this result with other separation theories leads to another conclusion: that layers which separate in moving equilibrium not only detach with the same mean profile shape, but detach at the same local pressure gradient.

Download or read book Integral Methods in the Theory of the Boundary Layer written by Lev Gerasimovich Loĭt͡si͡anskiĭ and published by . This book was released on 1944 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The application of the well-known basic principle of mechanics, the principle of Jourdain, to problems of the theory of the boundary layer leads to an equation from which the equations of Von Karman, Leibenson, and Golubev are derived as special cases. The given equation may be employed in other integral methods. The present paper deals with the method of the variation of the thickness of the boundary layer. A number of new approximate formulas valuable in aerodynamic calculations for the fristion distribution are derived from this procedure. The method has been applied only to laminar boundary layers, but it seems probable that it may be generalized to include turbulent layers as well.

Download or read book The Prediction of Turbulent Boundary Layer Separation Influenced by Blowing written by Arnold Polak and published by . This book was released on 1971 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents an analysis predicting separation of a turbulent boundary layer over a cone-flare configuration with gas injected into the boundary layer ahead of separation point. Separation location and separation lengths are compared with experimental data obtained at Mach number of 6 and a range of Reynolds numbers. At the highest Reynolds numbers the extent of separation decreases with increasing Reynolds number. When compared to separation over cylinder-flare body it is found that the extent of separation is lower for the cone-flare configuration. (Author).

Download or read book Laminar and Turbulent Separation Including Three dimensional Effects written by Von Karman Institute for Fluid Dynamics and published by . This book was released on 1974 with total page 254 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Incipient Separation of a Compressible Turbulent Boundary Layer written by Cyriel Appels and published by . This book was released on 1974 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Numerical Studies of Unsteady Laminar Boundary layer Separation Over Impulsively started Moving Objects written by Tzuyin Wu and published by . This book was released on 1991 with total page 504 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Separating Boundary Layer Response to an Unsteady Turbulent Environment written by David J Gwilliam (Jr) and published by . This book was released on 1989 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the separating boundary layer of a wing subjected to periodic turbulent disturbances was conducted. Turbulence pulses were generated by a non-thrusting spinning rod placed upstream of the test airfoil at the reduced frequencies of .09 and .47. Time-varying velocity measurements were made at various heights above the 70% chord location at 12 deg. angle of attack (nearly separated flow) and 22 deg. angle of attack (fully separated flow). Split-film anemometry was used to determine flow speed and direction. The flow responses were compared to the quasi-steady state of undisturbed separated flow. Variation of reduced frequency had a dramatic influence on the effects which the periodic disturbance had on the flow response. At a reduced disturbance of .47 the periodic disturbance had no noticeable influence. Imposition of periodic disturbance of the same reduced frequency on attached flow near separation (12 deg. angle of attack) once again caused no apparent destabilizing effects. Lack of sensitivity of the separated boundary layers to the pulses generated at the higher reduced frequency of .47 apparently resulted from its inability to resolve turbulent pulses from one another. Imposition at 22 deg. angle of attack of a pulse at the reduced frequency of .09, however, first stabilized the flow, then greatly intensified the original separation before allowing the flow to return to its undisturbed separated state.