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Heat Transfer And Pressure Distributions At A Mach Number Of 6 For 70 Deg Swept Slab Wings With Sharp And Spherical Noses And Cylindrical Leading Edges
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Book Synopsis Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges by :
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges by : Robert A. Jones
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by Robert A. Jones and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 40th AIAA Aerospace Sciences Meeting & Exhibit by :
Download or read book 40th AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2002 with total page 708 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1963 with total page 1196 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Jet Propulsion written by and published by . This book was released on 1961 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt: Beginning Oct. 1959 some issues include "Russian supplement."
Book Synopsis Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6 by : Louis G. Kaufman
Download or read book Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6 written by Louis G. Kaufman and published by . This book was released on 1979 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 by : Harold Mirels
Download or read book Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 written by Harold Mirels and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Book Synopsis Heat Transfer to a 70 Deg Swep Fin Partly Submerged in a Turbulent Boundary Layer at Mach 6 by :
Download or read book Heat Transfer to a 70 Deg Swep Fin Partly Submerged in a Turbulent Boundary Layer at Mach 6 written by and published by . This book was released on 1965 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Two-dimensional Multiple Sine-wave Protrusions on the Pressure and Heat-transfer Distributions for a Flat Plate at Mach 6 by : Aubrey M. Cary
Download or read book Effect of Two-dimensional Multiple Sine-wave Protrusions on the Pressure and Heat-transfer Distributions for a Flat Plate at Mach 6 written by Aubrey M. Cary and published by . This book was released on 1968 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 by : Barry Moskowitz
Download or read book Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 written by Barry Moskowitz and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Book Synopsis Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6 by :
Download or read book Pressure and Thermal Distributions on Wings and Adjacent Surfaces Induced by Elevon Deflections at Mach 6 written by and published by . This book was released on 1979 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Surface Pressure Tests on Blunt Slab Wings Swept to 0, 45, 60, and 70 Degrees at Mach Numbers 1.71, 2.5, 4.0, 7.6 and Angles of Attack Up to 40 Degrees by : FRANK H. DURGIN
Download or read book Surface Pressure Tests on Blunt Slab Wings Swept to 0, 45, 60, and 70 Degrees at Mach Numbers 1.71, 2.5, 4.0, 7.6 and Angles of Attack Up to 40 Degrees written by FRANK H. DURGIN and published by . This book was released on 1960 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the two-dimensional surface pressures on blunt, swept, slab wings was conducted. The test was undertaken as part of a more general program in which the flow field behind a blunt slab wing at high angles ofATTACK IN SUPERSONIC AND HYPERSONIC FLOW IS BEING STUDIED. The purpose of the present test was to determine experimentally the effects of leading edge blunting and sweep and angle of attack on the surface pressure distribution of a flat plate. Four models having 0, 45, 60, and 70 degrees of leading edge sweep were built, instrumented with 16 to 18 pressure taps and tested at Mach numbers 1.71, 2.5, 4.0, and 7.6 through an angle of attack range of -24 to 40 degrees. Each wing has a 3/8 inch cylindrical leading edge and flat upper, lower, and base surfaces. Tabulated and graphical presentation of the pressure data is included. (Author).
Book Synopsis Hypersonic and High Temperature Gas Dynamics by : John David Anderson
Download or read book Hypersonic and High Temperature Gas Dynamics written by John David Anderson and published by AIAA. This book was released on 1989 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.
Book Synopsis Heat-transfer and Pressure Measurements on a Concave-nose Cylinder for Mach Number Range of 2.49 to 4.44 by :
Download or read book Heat-transfer and Pressure Measurements on a Concave-nose Cylinder for Mach Number Range of 2.49 to 4.44 written by and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distribution Test of Sharp Leading-edge Wing and Wing-body Combinations at Mach 21 by : P. C. SHELTON
Download or read book Pressure Distribution Test of Sharp Leading-edge Wing and Wing-body Combinations at Mach 21 written by P. C. SHELTON and published by . This book was released on 1961 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distribution tests were made on a delta wing model and two wing-body combinations, all with sharp leading edges, in tunnel Hotshot 2 at a Mach number of 21 and a Reynolds number per foot of 400,000. Angle of attack ranged from -5 to +20 deg. Typical spanwise pressure distributions on the flat lower surface of model W4 are shown. It is observed that the pressure increases near the leading edge. The effect of adding the body to model W4 to obtain model W4B1 increases the pressure considerably over the entire lower surface. The spanwise pressure distribution of model (W-B)1 on the upper and lower surfaces is also shown. (Author).
Book Synopsis Aerodynamics of Wings and Bodies by : Holt Ashley
Download or read book Aerodynamics of Wings and Bodies written by Holt Ashley and published by Courier Corporation. This book was released on 1965-01-01 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt: This excellent, innovative reference offers a wealth of useful information and a solid background in the fundamentals of aerodynamics. Fluid mechanics, constant density inviscid flow, singular perturbation problems, viscosity, thin-wing and slender body theories, drag minimalization, and other essentials are addressed in a lively, literate manner and accompanied by diagrams.
Book Synopsis The Blunt Plate in Hypersonic Flow by : Donald Louis Baradell
Download or read book The Blunt Plate in Hypersonic Flow written by Donald Louis Baradell and published by . This book was released on 1960 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
