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An Experimental Investigation At A Mach Number Of 201 Of The Effects Of Body Cross Section Shape On The Aerodynamic Characteristics Of Bodies And Wing Body Combinations
Download An Experimental Investigation At A Mach Number Of 201 Of The Effects Of Body Cross Section Shape On The Aerodynamic Characteristics Of Bodies And Wing Body Combinations full books in PDF, epub, and Kindle. Read online An Experimental Investigation At A Mach Number Of 201 Of The Effects Of Body Cross Section Shape On The Aerodynamic Characteristics Of Bodies And Wing Body Combinations ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations by : Harry W. Carlson
Download or read book An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations written by Harry W. Carlson and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Book Synopsis Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations by : Langley Aeronautical Laboratory
Download or read book Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Book Synopsis Effect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63 by : Dennis E. Fuller
Download or read book Effect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63 written by Dennis E. Fuller and published by . This book was released on 1963 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0 ̊to 58 ̊and Mach Numbers from 0.6 to 2.0 by : Leland Howard Jorgensen
Download or read book Experimental Aerodynamic Characteristics for Bodies of Elliptic Cross Section at Angles of Attack from 0 ̊to 58 ̊and Mach Numbers from 0.6 to 2.0 written by Leland Howard Jorgensen and published by . This book was released on 1975 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the Ames 6- by 6-Foot Wind Tunnel to measure the static aerodynamic characteristics for two bodies of elliptic cross section and for their equivalent body of revolution. The equivalent body of revolution had the same length and axial distribution of cross-sectional area as the elliptic bodies. It consisted of a tangent ogive nose of fineness ratio 3 followed by a cylinder with a fineness ratio of 7. For the first body of elliptic cross section, the ratio of the semimajor axis to semiminor axis was held constant at 2 all along the body length. For the second elliptic body the nose was unchanged, but the aftersection was changed as follows: The cross-sectional axis ratio a/b was decreased from 2 to 1 over an axial distance of about 1.66 diam. Then, at this position, the a,b axis system was rotated 900, and the a/b ratio was increased back to 2 over the next 2.34 diam in length. Over the last length of three body diam, this rotated a/b ratio was held constant at 2.
Book Synopsis Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1.5 by : Dean R. Chapman
Download or read book Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1.5 written by Dean R. Chapman and published by . This book was released on 1947 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Tests were conducted to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested both with smooth surfaces and with roughness added to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. The principal geometric variables investigated were after-body shape and length-diameter ratio. For most models, force tests and base pressure measurements were made over a range of Reynolds numbers, based on model length, from 0.6 million to 5.0 millions. Schlieren photographs were used to analyze the effects of viscosity on flow separation and shock-wave configuration near the base and to verify the condition of the boundary layer as deduced from force tests. The results are discussed and compared with theoretical calculations.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1960 with total page 1006 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1988 with total page 520 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Body Shape on the Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6 by : Walter P. Nelms
Download or read book Effects of Body Shape on the Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6 written by Walter P. Nelms and published by . This book was released on 1972 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1990 with total page 1106 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Book Synopsis Aeronautical Engineering: A Cumulative Index to the 1984 Issues of the Continuing Bibliography by :
Download or read book Aeronautical Engineering: A Cumulative Index to the 1984 Issues of the Continuing Bibliography written by and published by . This book was released on 1985 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Reynolds Number Effects on the Induced Pressures of Cylindrical Bodies with Different Nose Shapes and Nose Drag Coefficients in Helium at a Mach Number of 24 by : Richard D. Wagner (Jr.)
Download or read book Reynolds Number Effects on the Induced Pressures of Cylindrical Bodies with Different Nose Shapes and Nose Drag Coefficients in Helium at a Mach Number of 24 written by Richard D. Wagner (Jr.) and published by . This book was released on 1963 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exact inviscid pressure distributions and shock shapes, obtained by the method of characteristics, are compared with experimental data. The results indicate a strong dependence of induced pressures upon Reynolds number, especially in the region immediately downstream of the nose-cylinder junction. The measured shock shapes revealed no discernible effect of Reynolds number variations.
Book Synopsis Calculated Effects of Body Shape on the Bow-shock Overpressures in the Far Field of Bodies in Supersonic Flow by : Donald L. Lansing
Download or read book Calculated Effects of Body Shape on the Bow-shock Overpressures in the Far Field of Bodies in Supersonic Flow written by Donald L. Lansing and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The theory developed by G.B. Whitham (Communications on Pure and Applied Mathematics, August 1952) for the supersonic flow about bodies in uniform flight in a homogeneous medium is reviewed and an integral which expresses the effect of body shape upon the flow parameters in the far field is reduced to a form which may be readily evaluated for arbitrary body shapes. This expression is then used to investigate the effect of nose angle, fineness ratio, and location of maximum body cross section upon the far-field pressure jump across the bow shock of slender bodies. Curves are presented showing the variation of the shock strength with each of these parameters. It is found that, for a wide variety of shapes having equal fineness ratios, the integral has nearly a constant value. Hence, to a first order, the pressure jump in the far field is independent of the shape and depends only upon the fineness ratio.
Book Synopsis A Parametric Study of the Aerodynamic Characteristics of Nose-cylinder-flare Bodies at a Mach Number of 6.0 by : George C. Ashby
Download or read book A Parametric Study of the Aerodynamic Characteristics of Nose-cylinder-flare Bodies at a Mach Number of 6.0 written by George C. Ashby and published by . This book was released on 1965 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1987 with total page 726 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Aerodynamic Performance of a Series of Power-law and Minimum-wave-drag Bodies at Mach 6 and Several Reynolds Numbers by : George C. Ashby
Download or read book Longitudinal Aerodynamic Performance of a Series of Power-law and Minimum-wave-drag Bodies at Mach 6 and Several Reynolds Numbers written by George C. Ashby and published by . This book was released on 1974 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds by : William R. Wimbrow
Download or read book Experimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds written by William R. Wimbrow and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local temperature recovery factors have been measured on two bodies of revolution at Mach numbers of 2.0 and are shown to be independent of Mach number, Reynolds number, or body shape. The measured recovery factor is well represented by the square root of Prandtl number for laminar boundary layers and by the cube root of Prandtl number for turbulent boundary layers, as predicted by theory.
Book Synopsis A Method for Calculating the Aerodynamic Loading on Wing-body Combinations at Small Angles of Attack in Supersonic Flow by : Charlie M. Jackson
Download or read book A Method for Calculating the Aerodynamic Loading on Wing-body Combinations at Small Angles of Attack in Supersonic Flow written by Charlie M. Jackson and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration. In order to provide a basis for evaluation of the method, experimental measurements of surface pressures, forces, and moments were made on a series of basic wing-body configurations over a Mach number range from 2.5 to 4.5. Comparison of the theoretical estimates with these experimental data generally indicated good agreement for the entire range of configurations and test conditions.
