The Effect Of Pressure Gradients On Transition Zone Length In Hypersonic Boundary Layers

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The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers

Author : Roger L. Kimmel
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers by : Roger L. Kimmel

Download or read book The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers written by Roger L. Kimmel and published by . This book was released on 1993 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7 degrees half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.

Global Stability Analysis of Shear Flows

Author : Rameshkumar Bhoraniya
Publisher : Springer Nature
ISBN 13 : 9811995745
Total Pages : 232 pages
Book Rating : 4.8/5 (119 download)

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Book Synopsis Global Stability Analysis of Shear Flows by : Rameshkumar Bhoraniya

Download or read book Global Stability Analysis of Shear Flows written by Rameshkumar Bhoraniya and published by Springer Nature. This book was released on 2023-03-10 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book presents the fundamentals and advanced research on the global stability analysis of the shear flows. The contents investigate the results of global stability analysis for different configurations of internal and external shear flows. The topics covered are global stability analysis of converging-diverging channel flows, axisymmetric boundary layer developed on a circular cylinder, cone and inclined flat-plate boundary layer, and wall jets. It further explains the effect of divergence, convergence, transverse curvature, and pressure gradients on the global stability of the different configurations of shear flows. The book is a valuable reference for beginners, researchers, and professionals working in the field of aerodynamics and marine hydrodynamics.

Comments on Hypersonic Boundary-layer Transition

Author : Kenneth F. Stetson
Publisher :
ISBN 13 :
Total Pages : 116 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Comments on Hypersonic Boundary-layer Transition by : Kenneth F. Stetson

Download or read book Comments on Hypersonic Boundary-layer Transition written by Kenneth F. Stetson and published by . This book was released on 1990 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.

Factors Affecting Transition at Supersonic Speeds

Author : K. R. Czarnecki
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Factors Affecting Transition at Supersonic Speeds by : K. R. Czarnecki

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.

41st AIAA Aerospace Sciences Meeting & Exhibit

Author :
Publisher :
ISBN 13 :
Total Pages : 672 pages
Book Rating : 4.0/5 ( download)

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Book Synopsis 41st AIAA Aerospace Sciences Meeting & Exhibit by :

Download or read book 41st AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2003 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Boundary Layer Transition at Supersonic Speeds

Author : E. R. Van Driest
Publisher :
ISBN 13 :
Total Pages : 108 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Boundary Layer Transition at Supersonic Speeds by : E. R. Van Driest

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.

Transitional and Turbulent Compressible Flows, 1993

Author : L. D. Kral
Publisher :
ISBN 13 :
Total Pages : 274 pages
Book Rating : 4.F/5 ( download)

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Book Synopsis Transitional and Turbulent Compressible Flows, 1993 by : L. D. Kral

Download or read book Transitional and Turbulent Compressible Flows, 1993 written by L. D. Kral and published by . This book was released on 1993 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Transitional and Turbulent Compressible Flows

Author :
Publisher :
ISBN 13 :
Total Pages : 278 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Transitional and Turbulent Compressible Flows by :

Download or read book Transitional and Turbulent Compressible Flows written by and published by . This book was released on 1993 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Boundary Layer Effects

Author : Anthony W. Fiore
Publisher :
ISBN 13 :
Total Pages : 962 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Boundary Layer Effects by : Anthony W. Fiore

Download or read book Boundary Layer Effects written by Anthony W. Fiore and published by . This book was released on 1978 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.

Scientific and Technical Aerospace Reports

Author :
Publisher :
ISBN 13 :
Total Pages : 584 pages
Book Rating : 4.:/5 (3 download)

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Book Synopsis Scientific and Technical Aerospace Reports by :

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 584 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Journal of Fluids Engineering

Author :
Publisher :
ISBN 13 :
Total Pages : 888 pages
Book Rating : 4.:/5 (318 download)

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Book Synopsis Journal of Fluids Engineering by :

Download or read book Journal of Fluids Engineering written by and published by . This book was released on 1998 with total page 888 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Applied Mechanics Reviews

Author :
Publisher :
ISBN 13 :
Total Pages : 776 pages
Book Rating : 4.:/5 (26 download)

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Book Synopsis Applied Mechanics Reviews by :

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1971 with total page 776 pages. Available in PDF, EPUB and Kindle. Book excerpt:

31st International Symposium on Shock Waves 1

Author : Akihiro Sasoh
Publisher : Springer
ISBN 13 : 3319910205
Total Pages : 1188 pages
Book Rating : 4.3/5 (199 download)

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Book Synopsis 31st International Symposium on Shock Waves 1 by : Akihiro Sasoh

Download or read book 31st International Symposium on Shock Waves 1 written by Akihiro Sasoh and published by Springer. This book was released on 2019-03-21 with total page 1188 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the first volume of a two volume set which presents the results of the 31st International Symposium on Shock Waves (ISSW31), held in Nagoya, Japan in 2017. It was organized with support from the International Shock Wave Institute (ISWI), Shock Wave Research Society of Japan, School of Engineering of Nagoya University, and other societies, organizations, governments and industry. The ISSW31 focused on the following areas: Blast waves, chemical reacting flows, chemical kinetics, detonation and combustion, ignition, facilities, diagnostics, flow visualization, spectroscopy, numerical methods, shock waves in rarefied flows, shock waves in dense gases, shock waves in liquids, shock waves in solids, impact and compaction, supersonic jet, multiphase flow, plasmas, magnetohyrdrodynamics, propulsion, shock waves in internal flows, pseudo-shock wave and shock train, nozzle flow, re-entry gasdynamics, shock waves in space, Richtmyer-Meshkov instability, shock/boundary layer interaction, shock/vortex interaction, shock wave reflection/interaction, shock wave interaction with dusty media, shock wave interaction with granular media, shock wave interaction with porous media, shock wave interaction with obstacles, supersonic and hypersonic flows, sonic boom, shock wave focusing, safety against shock loading, shock waves for material processing, shock-like phenomena, and shock wave education. These proceedings contain the papers presented at the symposium and serve as a reference for the participants of the ISSW 31 and individuals interested in these fields.

AIAA Journal

Author : American Institute of Aeronautics and Astronautics
Publisher :
ISBN 13 :
Total Pages : 1358 pages
Book Rating : 4.F/5 ( download)

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Book Synopsis AIAA Journal by : American Institute of Aeronautics and Astronautics

Download or read book AIAA Journal written by American Institute of Aeronautics and Astronautics and published by . This book was released on 2002 with total page 1358 pages. Available in PDF, EPUB and Kindle. Book excerpt:

18th AIAA Aerospace Ground Testing Conference

Author :
Publisher :
ISBN 13 :
Total Pages : 618 pages
Book Rating : 4.0/5 ( download)

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Book Synopsis 18th AIAA Aerospace Ground Testing Conference by :

Download or read book 18th AIAA Aerospace Ground Testing Conference written by and published by . This book was released on 1994 with total page 618 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition

Author : J. Leith Potter
Publisher :
ISBN 13 :
Total Pages : 166 pages
Book Rating : 4.3/5 (91 download)

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Book Synopsis Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition by : J. Leith Potter

Download or read book Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition written by J. Leith Potter and published by . This book was released on 1960 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitudinal extent of the boundary layer from beginning to end of transition, the distribution of fluctuation energy in the laminar layer, and effectiveness of surface roughness in promoting transition. A critical layer of intense local energy fluctuations was found at all Mach numbers studied. The existence of such a critical layer is predicted by stability theory. Hot-wire surveys of the laminar, transitional, and turbulent boundary layers are presented to illustrate the critical layer in laminar flow and subsequent development into the transition process. The relation between boundary layer transition on flat plates and cones in supersonic flow is explored and a process for correcting data to account for leading edge bluntness is devised. On the basis of a comparison of data corrected for the effects of leading edge geometry, it is shown that the Reynolds umber of transition on a cone is three times that on a vanishingly thin flate plate. Close agreement between data from various wind tunnels is demonstrated. Study of the effect of finite leading edges yields significant illustrations of the influence of unit Reynolds number on boundary layer transition. A correlation of the effects of surface roughness on transition is achieved. This treatment includes two- and three-dimensional roughness in both subsonic and supersonic streams. At this time only zero pressure gradients have been studied. The entire range of movement of transition from its position with no roughness up to its reaching the roughness element is describable by the procedure give. Examples of application of the correlation results show excellent agreement with experimental data from a variety of sources. Implications concerning tripping hypersonic boundary layers are discussed.

Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data

Download Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data PDF Online Free

Author : Julius E. Harris
Publisher :
ISBN 13 :
Total Pages : 92 pages
Book Rating : 4.:/5 (31 download)

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Book Synopsis Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data by : Julius E. Harris

Download or read book Numerical Solution of the Equations for Compressible Laminar, Transitional, and Turbulent Boundary Layers and Comparisons with Experimental Data written by Julius E. Harris and published by . This book was released on 1971 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical method for solving the equations for laminar, transitional, and turbulent compressible boundary layers for either planar or axisymmetric flows is presented. The fully developed turbulent region is treated by replacing the Reynolds stress terms with an eddy viscosity model. The mean properties of the transitional boundary layer are calculated by multiplying the eddy viscosity by an intermittency function based on the statistical production and growth of the turbulent spots. A specifiable turbulent Prandtl number relates the turbulent flux of heat to the eddy viscosity. A three-point implicit finite-difference scheme is used to solve the system of equations. The momentum and energy equations are solved simultaneously without iteration. Numerous test cases are compared with experimental data for supersonic and hypersonic flows; these cases include flows with both favorable and mildly unfavorable pressure gradient histories, mass flux at the wall, and traverse curvature.