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Author : Laura L. Pauley
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book A Numerical Investigation of Supersonic Nozzle Boundary Layer Transition written by Laura L. Pauley and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William D. Harvey
Publisher :
ISBN 13 :
Total Pages : 92 pages
Book Rating : 4.:/5 (31 download)
Download or read book Experimental and Numerical Investigation of Boundary-layer Development and Transition on the Walls of a Mach 5 Nozzle written by William D. Harvey and published by . This book was released on 1975 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 232 pages
Book Rating : 4.:/5 (318 download)
Download or read book Numerical Investigation of Transition in Supersonic Boundary Layers Using DNS and LES. written by and published by . This book was released on 2008 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work focuses on instability mechanisms of high-speed boundary layers over flat plates and cones with a circular cross section. Supersonic transition investigations at Mach 2 and hypersonic transition investigations at Mach 8 are performed using Direct Numerical Simulations (DNS). At wind-tunnel conditions, these simulations allow for comparison with experimental measurements to verify fundamental stability characteristics. For the DNS of boundary-layer transition at Mach 2, the experimental studies by Kosinov et al. (1994) and Ermolaev et al. (1996) for a flat plate serve as reference and provide the physical conditions for the numerical setup. In these experiments, the weakly nonlinear regime of transition was studied resulting in the discovery of asymmetric subharmonic resonance triads. Scrutinizing the experimental data, reveals however the presence of another, possibly competing breakdown mechanism, in the experiments. Both mechanisms were addressed in detail in this work. To better understand geometrical influences, flat-plate and cylindrical geometries are studied under after-shock conditions of the conical investigations (experiments). This allows for a direct comparison with the results of the sharp cone to evaluate the influence of spanwise curvature and cone opening angle. The ratio of the boundary layer thickness to the spanwise radius is used to determine the importance of spanwise curvature effects. For a cone, in downstream direction the radius increases linearly while the boundary layer thickness stays almost constant. Hence, spanwise curvature effects are strongest close to the nose tip and decrease in downstream direction. Their influences on the secondary instability mechanisms provide some preliminary guidance in the design for future high-speed air vehicles.
Download or read book יסודות המילים written by and published by . This book was released on 1973 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edwin Snow Gallacher
Publisher :
ISBN 13 :
Total Pages : 214 pages
Book Rating : 4.E/5 ( download)
Download or read book Theoretical Investigation of a Boundary Layer and Heat Transfer in a Supersonic Nozzle written by Edwin Snow Gallacher and published by . This book was released on 1950 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Thierry Maeder
Publisher :
ISBN 13 : 9783183394074
Total Pages : 119 pages
Book Rating : 4.3/5 (94 download)
Download or read book Numerical Investigation of Supersonic Turbulent Boundary Layers written by Thierry Maeder and published by . This book was released on 2000 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : E. R. Van Driest
Publisher :
ISBN 13 :
Total Pages : 108 pages
Book Rating : 4.3/5 (91 download)
Download or read book Boundary Layer Transition at Supersonic Speeds written by E. R. Van Driest and published by . This book was released on 1961 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
Author : Donald Eckhart Emerson
Publisher :
ISBN 13 :
Total Pages : 246 pages
Book Rating : 4.:/5 (21 download)
Download or read book Investigation of a Thick Laminar Boundary Layer in a Supersonic Nozzle written by Donald Eckhart Emerson and published by . This book was released on 1951 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
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ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (227 download)
Download or read book Investigation of Supersonic Boundary Layer Transition and Turbulent Structure written by and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This final report describes the research progress made possible with the equipment purchased under this grant, and the manpower supplied by Princeton University as part of cost sharing.
Author :
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ISBN 13 :
Total Pages : 616 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA Technical Note written by and published by . This book was released on 1975 with total page 616 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William A. Cassels
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (31 download)
Download or read book Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds written by William A. Cassels and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author : Robert W. Higgins
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow written by Robert W. Higgins and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition has been studied on a heated flat plate in an air stream at a Mach number of 2.40 and a length Reynolds number range from 475,000 to 3,930,000. The transition region was investigated at nominal plate temperature levels of 60, 100, 140, 180, and 260 degrees F and depicted in a series of curves of transition Reynolds numbers, based on boundary-layer dimensions and fluid properties evaluated alternatively at free-stream and wall temperatures. The average skin-friction coefficient over the laminar portion of the boundary layer was determined.
Download or read book NASA Technical Paper written by and published by . This book was released on 1981 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
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ISBN 13 :
Total Pages : 424 pages
Book Rating : 4.0/5 ( download)
Download or read book AIAA/NASA/OAI Conference on Advanced SEI Technologies: 91-3550 - 91-3594 written by and published by . This book was released on 1991 with total page 424 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Richard D. Sandberg
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (139 download)
Download or read book Numerical Investigation of Transitional and Turbulent Supersonic Axisymmetric Wakes (PHD). written by Richard D. Sandberg and published by . This book was released on with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : K. R. Czarnecki
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.3/5 (91 download)
Download or read book Factors Affecting Transition at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1953 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper surveys the available material and summarizes what is known to date about boundary-layer transition at supersonic speeds. Variables studied include Mach number, Reynolds number, pressure gradients, heat transfer, surface roughness, and angle of attack. The discussion is limited to bodies of revolution because similar reliable data for wings is lacking.
Author :
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ISBN 13 :
Total Pages : 704 pages
Book Rating : 4.:/5 (31 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
