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Experimental Pressure Distributions For A Family Of Blunt Bodies At Mach Numbers From 249 To 463 And Angles Of Attack From 0 To 15
Download Experimental Pressure Distributions For A Family Of Blunt Bodies At Mach Numbers From 249 To 463 And Angles Of Attack From 0 To 15 full books in PDF, epub, and Kindle. Read online Experimental Pressure Distributions For A Family Of Blunt Bodies At Mach Numbers From 249 To 463 And Angles Of Attack From 0 To 15 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 Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 by : Peter T. Bernot
Download or read book Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 written by Peter T. Bernot and published by . This book was released on 1963 with total page 0 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 Pressure Tests on the Standard Hypervelocity Ballistic Model HB-2 at Mach 1.5 to 5 by : Jerry H. Jones
Download or read book Pressure Tests on the Standard Hypervelocity Ballistic Model HB-2 at Mach 1.5 to 5 written by Jerry H. Jones and published by . This book was released on 1964 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure tests were conducted on a standard hypervelocity ballistic model HB-2 in the 40 in. supersonic Tunnel A of the von Karman Gas Dynamics Facility. Data were obtained at Mach numbers 1.5, 3, and 5 at angles of attack of 0, 3, 5, 10, and 15 deg, and at Mach numbers 2 and 4 at zero angle of attack. Reynolds number, based on the centerbody diameter, ranged from 0.32 x 1,000,000 to 2.3 x 1,000,000. Pressure distributions are presented, and a comparison is made of force and moment coefficients obtained from integrated pressure data with results from previous force tests on this model. (Author).
Book Synopsis Wind Tunnel Tests on Blunt Body Explosively Formed Projectile by :
Download or read book Wind Tunnel Tests on Blunt Body Explosively Formed Projectile written by and published by . This book was released on 1995 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: Describes supersonic wind tunnel tests in a 0.6-by-0.6-metre indraft facility to study the flight dynamic stability of a particular explosively-formed projectile configuration named Blunt Body. The tests were intended to gather experimental data on surface static pressure distribution and aerodynamic stability coefficients. Results are presented for tests made with a 6-blunt-fin explosively-formed projectile model. The model configuration was obtained from high-speed photography of various real projectiles in flight. A total of 107 runs were made at Mach numbers of 2.97, 3.50, and 3.99, for a variety of roll angles and angles of attack up to 15 degrees. Equations used for data treatment are included as well as a description of the instrumentation test setting and several model drawings. Comparisons are also made to results of computational fluid dynamics simulations.
Book Synopsis Aerodynamic Performance and Static Stability Characteristics of a Blunt Nosed, Boattailed, 13 Deg Half Cone at Mach Numbers from 0.6 to 5.0 by :
Download or read book Aerodynamic Performance and Static Stability Characteristics of a Blunt Nosed, Boattailed, 13 Deg Half Cone at Mach Numbers from 0.6 to 5.0 written by and published by . This book was released on 1961 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of the Static Pressure Distributions and Shock Shape on an Oblate Spheroid at Mach Numbers of 3 and 6 by :
Download or read book Measurements of the Static Pressure Distributions and Shock Shape on an Oblate Spheroid at Mach Numbers of 3 and 6 written by and published by . This book was released on 1966 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of experimental measurements of the static pressure distribution and bow shock shape on an oblate spheroid are presented. This experiment was conducted at nominal Mach numbers of 3 and 6 and a free stream Reynolds number range of 2,300,000 to 5,800,000 per foot. Comparisons are made with the calculated values of several different laboratories.
Book Synopsis Pressure Distributions on Triangular and Rectangular Wings to High Angles of Attack - Mach Numbers 1.45 and 1.97 by : George E. Kaattari
Download or read book Pressure Distributions on Triangular and Rectangular Wings to High Angles of Attack - Mach Numbers 1.45 and 1.97 written by George E. Kaattari and published by . This book was released on 1954 with total page 27 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 Introduction to Aircraft Flight Mechanics by : Thomas R. Yechout
Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Book Synopsis Surface Pressure Tests on Blunt Slab Wings Swept at 0, 45°, 60° and 70° at Mach Numbers 1.71, 2.5, 4.0, 7.6 and Angles of Attack Up to 40° by : Frank Herman Durgin
Download or read book Surface Pressure Tests on Blunt Slab Wings Swept at 0, 45°, 60° and 70° at Mach Numbers 1.71, 2.5, 4.0, 7.6 and Angles of Attack Up to 40° written by Frank Herman Durgin and published by . This book was released on 1960 with total page 71 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerofoil Sections by : Friedrich Wilhelm Riegels
Download or read book Aerofoil Sections written by Friedrich Wilhelm Riegels and published by . This book was released on 1961 with total page 281 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Speed Wind Tunnel Testing by : Jewel B. Barlow
Download or read book Low-Speed Wind Tunnel Testing written by Jewel B. Barlow and published by John Wiley & Sons. This book was released on 1999-02-22 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A brand-new edition of the classic guide on low-speed wind tunnel testing While great advances in theoretical and computational methods have been made in recent years, low-speed wind tunnel testing remains essential for obtaining the full range of data needed to guide detailed design decisions for many practical engineering problems. This long-awaited Third Edition of William H. Rae, Jr.'s landmark reference brings together essential information on all aspects of low-speed wind tunnel design, analysis, testing, and instrumentation in one easy-to-use resource. Written by authors who are among the most respected wind tunnel engineers in the world, this edition has been updated to address current topics and applications, and includes coverage of digital electronics, new instrumentation, video and photographic methods, pressure-sensitive paint, and liquid crystal-based measurement methods. The book is organized for quick access to topics of interest, and examines basic test techniques and objectives of modeling and testing aircraft designs in low-speed wind tunnels, as well as applications to fluid motion analysis, automobiles, marine vessels, buildings, bridges, and other structures subject to wind loading. Supplemented with real-world examples throughout, Low-Speed Wind Tunnel Testing, Third Edition is an indispensable resource for aerospace engineering students and professionals, engineers and researchers in the automotive industries, wind tunnel designers, architects, and others who need to get the most from low-speed wind tunnel technology and experiments in their work.
Download or read book Pentagon 9/11 written by Alfred Goldberg and published by Office of the Secretary, Historical Offi. This book was released on 2007-09-05 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: The most comprehensive account to date of the 9/11 attack on the Pentagon and aftermath, this volume includes unprecedented details on the impact on the Pentagon building and personnel and the scope of the rescue, recovery, and caregiving effort. It features 32 pages of photographs and more than a dozen diagrams and illustrations not previously available.
Book Synopsis Theory of Wing Sections by : Ira H. Abbott
Download or read book Theory of Wing Sections written by Ira H. Abbott and published by Courier Corporation. This book was released on 2012-04-26 with total page 708 pages. Available in PDF, EPUB and Kindle. Book excerpt: Concise compilation of subsonic aerodynamic characteristics of NACA wing sections, plus description of theory. 350 pages of tables.
Book Synopsis The Encyclopedia of Aerodynamics by : Frank Hitchens
Download or read book The Encyclopedia of Aerodynamics written by Frank Hitchens and published by Andrews UK Limited. This book was released on 2015-11-25 with total page 677 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Encyclopedia of Aerodynamics was written for pilots at all levels from private pilot to airline pilot, military pilots and students of aerodynamics as a complete reference manual to aerodynamic terminology. General aerodynamic text books for pilots are relatively limited in their scope while aerodynamic text books for engineering students involve complex calculus. The references in this book, The Encyclopedia of Aerodynamics, are clearly described and only basic algebra is used in a few references but is completely devoid of any calculus - an advantage to many readers. Over 1400 references are included with alternative terms used where appropriate and cross-referenced throughout. The text is illustrated with 178 photographs and 96 diagrams. The Encyclopedia of Aerodynamics is an ideal aerodynamic reference manual for any pilot's bookshelf.
Book Synopsis Parachute Recovery Systems by : Theo W. Knacke
Download or read book Parachute Recovery Systems written by Theo W. Knacke and published by . This book was released on 1992 with total page 524 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this manual is to provide recovery system engineers in government and industry with tools to evaluate, analyze, select, and design parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, concept analysis, parachute performance, force and stress analysis, material selection, parachute assembly and component design, and manufacturing. Experienced recovery system engineers will find this publication useful as a technical reference book; recent college graduates will find it useful as a textbook for learning about parachutes and parachute recovery systems; and technicians with extensive practical experience will find it useful as an engineering textbook that includes a chapter on parachute- related aerodynamics. In this manual, emphasis is placed on aiding government employees in evaluating and supervising the design and application of parachute systems. The parachute recovery system uses aerodynamic drag to decelerate people and equipment moving in air from a higher velocity to a lower velocity and to a safe landing. This lower velocity is known as rate of descent, landing velocity, or impact velocity, and is determined by the following requirements: (1) landing personnel uninjured and ready for action, (2) landing equipment and air vehicles undamaged and ready for use or refurbishment, and (3) impacting ordnance at a preselected angle and velocity.
