Experimental Magnus and Static Stability Characteristics of Ballistic Projectiles with Various Boattail Angles and Lengths at Mach Numbers from 0.5 Through 2.5 PDF Download

Author: Leroy M. Jenke
Publisher:
ISBN:
Category : Ballistics
Languages : en
Pages : 134

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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16

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Author: H. Ginsberg
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

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The report documents studies to determine experimentally the effect of thrusting-jet specific heat ratios on missile model base pressure. The tests were conducted at a freestream Mach number of 2.18 over a wide range of jet static to freestream static pressure ratios. Variation of the specific heat ratios was obtained by the use of different jet gases. Jet static pressure ratios up to 40 have been covered. Flow interference effects were held to a minimum by mounting the model on a support attached to a strut in the plenum chamber of the wind tunnel and reaching through the wind tunnel nozzle throat into the test section. The effects of molecular weight (at gamma = 1.66) on base pressure were briefly investigated. A molecular weight shift from 40 to 29 showed only a slight effect on base pressure, however, a shift from 29 to 4 increased the base pressure coefficient an average of 0.04 or approximately 20% of the minimum value. It was observed in this investigation that the base pressure reached its minimum value at a freestream-to-jet molecular weight ratio of unity for all jet static pressure ratios tested. Extension areas recommended for further investigation include the determination of jet-specific-heat ratio, jet temperature and molecular-weight effects on base pressure when freestream conditions and model afterbody geometry are systematically varied. (Author).

Author: L. E. RITTENHOUSE
Publisher:
ISBN:
Category :
Languages : en
Pages : 1

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Static stability and axial-force data are presented for a recoverable data capsule consisting of a flat-nose cylinder with an extensible flare at Mach numbers from 0.60 through 1.50 and angles of attack from -3 deg to +8 deg. The capsule was found to be statically stable throughout the Mach number and angle-of-attack range for a center-of-gravity location no further aft than 55 percent of the body length. The static stability characteristics of the capsule at Mach numbers less than 1.10 indicate the strong possibility of dynamic instability. Moreover, comments are made regarding the flow field adjacent to the model. (Author).

Author: Theo W. Knacke
Publisher:
ISBN:
Category : Sports & Recreation
Languages : en
Pages : 524

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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.

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 132

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Author: Lawrence R. Benson
Publisher:
ISBN: 9781626830042
Category : Aerodynamics, Supersonic
Languages : en
Pages : 388

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Author: Jewel B. Barlow
Publisher: John Wiley & Sons
ISBN: 0471557749
Category : Technology & Engineering
Languages : en
Pages : 738

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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.

Author: T.A. Heppenheimer
Publisher: Courier Dover Publications
ISBN: 0486834514
Category : Technology & Engineering
Languages : en
Pages : 355

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This volume from The NASA History Series presents an overview of the science of hypersonics, the study of flight at speeds at which the physics of flows is dominated by aerodynamic heating. The survey begins during the years immediately following World War II, with the first steps in hypersonic research: the development of missile nose cones and the X-15; the earliest concepts of hypersonic propulsion; and the origin of the scramjet engine. Next, it addresses the re-entry problem, which came to the forefront during the mid-1950s, showing how work in this area supported the manned space program and contributed to the development of the orbital shuttle. Subsequent chapters explore the fading of scramjet studies and the rise of the National Aerospace Plane (NASP) program of 1985–95, which sought to lay groundwork for single-stage vehicles. The program's ultimate shortcomings — in terms of aerodynamics, propulsion, and materials — are discussed, and the book concludes with a look at hypersonics in the post-NASP era, including the development of the X-33 and X-34 launch vehicles, further uses for scramjets, and advances in fluid mechanics. Clearly, ongoing research in hypersonics has yet to reach its full potential, and readers with an interest in aeronautics and astronautics will find this book a fascinating exploration of the field's history and future.

Author: Joseph R. Chambers
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 406

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