Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Experimental Pressure Distributions Over Blunt Two And Three Dimensional Bodies Having Similar Cross Sections At A Mach Number Of 495
Download Experimental Pressure Distributions Over Blunt Two And Three Dimensional Bodies Having Similar Cross Sections At A Mach Number Of 495 full books in PDF, epub, and Kindle. Read online Experimental Pressure Distributions Over Blunt Two And Three Dimensional Bodies Having Similar Cross Sections At A Mach Number Of 495 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Experimental Pressure Distributions Over Blunt Two- and Three-dimensional Bodies Having Similar Cross Sections at a Mach Number of 4.95 by : Jerome D. Julius
Download or read book Experimental Pressure Distributions Over Blunt Two- and Three-dimensional Bodies Having Similar Cross Sections at a Mach Number of 4.95 written by Jerome D. Julius and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow by : Mitchel H. Bertram
Download or read book An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Book Synopsis NASA Technical Report by : United States. National Aeronautics and Space Administration
Download or read book NASA Technical Report written by United States. National Aeronautics and Space Administration and published by . This book was released on 1963 with total page 892 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 1967 with total page 686 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 1993 with total page 712 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 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.
Download or read book NASA SP. written by and published by . This book was released on 1992 with total page 548 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1966 with total page 1492 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 1998 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. Government Research Reports by :
Download or read book U.S. Government Research Reports written by and published by . This book was released on 1959 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 287) by :
Download or read book Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 287) written by and published by . This book was released on 1993 with total page 706 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Comparison of the Experimental Subsonic Pressure Distributions about Several Bodies of Revolution with Pressure Distributions Computed by Means of the Linearized Theory by : Clarence W. Matthews
Download or read book A Comparison of the Experimental Subsonic Pressure Distributions about Several Bodies of Revolution with Pressure Distributions Computed by Means of the Linearized Theory written by Clarence W. Matthews and published by . This book was released on 1952 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comparison is made of the theoretical and experimental subsonic compressible pressure-coefficient distributions about several bodies in revolution. The results show that the linearized theory predicts the subsonic pressure coefficients over the central portion of the body. An extrapolation of the theory into the supercritical range does not predict the rearward shift of the negative pressure peak which occurs after the flow becomes critical. Two equations are presented for approximately determining the subsonic compressible pressure-coefficient distributions from the incompressible distribtutions.
Book Synopsis Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range by : John M. Swihart
Download or read book Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range written by John M. Swihart and published by . This book was released on 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 106 to 39 x 106, and on maximum diameter from 1.35 x 105 to 4.53 x 105. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Book Synopsis Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 235) by :
Download or read book Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 235) written by and published by . This book was released on 1989 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 U.S. Government Research & Development Reports by :
Download or read book U.S. Government Research & Development Reports written by and published by . This book was released on 1966-11 with total page 1014 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distribution and Some Effects of Viscosity on Slender Inclined Bodies of Revolution by : H. Julian Allen
Download or read book Pressure Distribution and Some Effects of Viscosity on Slender Inclined Bodies of Revolution written by H. Julian Allen and published by . This book was released on 1950 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The simplified solution for the pressure distribution of slender inclined bodies of revolution is developed. The solution should be suitable for bodies of high fineness ratio even at low supersonic speeds, provided the angle of attack is small. Comparison with low-speed experimental results indicates that the observed flow separation phenomena can be explained in terms of the calculated pressure distributions together with the theory of oblique viscous flows.
