Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Isolated Performance At Mach Numbers From 060 To 286 Of Several Expendable Nozzle Concepts For Supersonic Applications
Download Isolated Performance At Mach Numbers From 060 To 286 Of Several Expendable Nozzle Concepts For Supersonic Applications full books in PDF, epub, and Kindle. Read online Isolated Performance At Mach Numbers From 060 To 286 Of Several Expendable Nozzle Concepts For Supersonic Applications ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Isolated Performance at Mach Numbers From 0.60 to 2.86 of Several Expendable Nozzle Concepts for Supersonic Applications by : Richard J. Re
Download or read book Isolated Performance at Mach Numbers From 0.60 to 2.86 of Several Expendable Nozzle Concepts for Supersonic Applications written by Richard J. Re and published by . This book was released on 2001 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt: Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Winf Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of O° to determine the isolated performane of several expendable nozzle concepts for supersonic noaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ration, and cruciform shroud flap vectoring were investigated. The nozzle pressure ration range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan WInd Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721101832 Total Pages :200 pages Book Rating :4.1/5 (18 download)
Book Synopsis Isolated Performance at Mach Numbers from 0. 60 to 2. 86 of Several Expendable Nozzle Concepts for Supersonic Applications by : National Aeronautics and Space Administration (NASA)
Download or read book Isolated Performance at Mach Numbers from 0. 60 to 2. 86 of Several Expendable Nozzle Concepts for Supersonic Applications written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Wind Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of 0 deg to determine the isolated performance of several expendable nozzle concepts for supersonic nonaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ratio, and cruciform shroud flap vectoring were investigated. The nozzle pressure ratio range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan Wind Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured. The shortest nozzle had the best thrust-minus-drag performance at Mach numbers up to 0.95 but was approached in performance by other configurations at Mach numbers of 1.15 and 1.25. At Mach numbers above 1.25, the cruciform nozzle configuration having the same expansion ratio (2.64) as the fixed geometry nozzles had the best thrust-minus-drag performance. Ventilation of the fixed geometry divergent shrouds to the nozzle external boattail flow generally improved thrust-minus-drag performance at Mach numbers from 0.60 to 1.25, but decreased performance above a Mach number of 1.25. Re, Richard J. and Berrier, Bobby L. and Abeyounis, William K. Langley Research Center RTOP 706-17-21-05
Book Synopsis Parametric Investigation of Single-expansion-ramp Nozzles at Mach Numbers from 0.60 to 1.20 by : Francis J. Capone
Download or read book Parametric Investigation of Single-expansion-ramp Nozzles at Mach Numbers from 0.60 to 1.20 written by Francis J. Capone and published by . This book was released on 1992 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 by : John R. Carlson
Download or read book Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 written by John R. Carlson and published by . This book was released on 1994 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Aerodynamic Design and Calibration of an Asymmetric Variable Mach Number Nozzle with Sliding Block for the Mach Number Range 1.27 to 2.75 by : Paige B. Burbank
Download or read book The Aerodynamic Design and Calibration of an Asymmetric Variable Mach Number Nozzle with Sliding Block for the Mach Number Range 1.27 to 2.75 written by Paige B. Burbank and published by . This book was released on 1951 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of designing an aymmetric, fixed-geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was a constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.02 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Book Synopsis Thrust Performance of Isolated Plug Nozzles with Two Types of 40-spoke Noise Suppressor at Mach Numbers from 0 to 0.45 by : Douglas E. Harrington
Download or read book Thrust Performance of Isolated Plug Nozzles with Two Types of 40-spoke Noise Suppressor at Mach Numbers from 0 to 0.45 written by Douglas E. Harrington and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 1.5 to 4.0. In addition, an unsuppressed plug nozzle and a Supersonic Tunnel Association nozzle were also tested to provide baseline levels of thrust performance. The unsuppressed plug nozzle had an efficiency of 98 percent at an assumed takeoff pressure ratio of 3.0 and at Mach 0.36. At the same condition the suppressor nozzles had efficiencies of approximately 83.5 percent.
Book Synopsis Thrust Performance of Isolated 36-chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0.45 by : Douglas E. Harrington
Download or read book Thrust Performance of Isolated 36-chute Suppressor Plug Nozzles with and Without Ejectors at Mach Numbers from 0 to 0.45 written by Douglas E. Harrington and published by . This book was released on 1975 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of an Isolated Two-dimensional Variable-geometry Wedge Nozzle with Translating Shroud and Collapsing Wedge at Speeds Up to Mach 2.01 by : Donald L. Maiden
Download or read book Performance of an Isolated Two-dimensional Variable-geometry Wedge Nozzle with Translating Shroud and Collapsing Wedge at Speeds Up to Mach 2.01 written by Donald L. Maiden and published by . This book was released on 1975 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45 by : Douglas E. Harrington
Download or read book Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45 written by Douglas E. Harrington and published by . This book was released on 1976 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of an Isolated Two-dimensional Wedge Nozzle with Fixed Cowl and Variable Wedge Centerbody at Mach Numbers Up to 2.01 by : Donald L. Maiden
Download or read book Performance of an Isolated Two-dimensional Wedge Nozzle with Fixed Cowl and Variable Wedge Centerbody at Mach Numbers Up to 2.01 written by Donald L. Maiden and published by . This book was released on 1976 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Evaluation of Expendable Supersonic Nozzle Concepts by : B. Vittal
Download or read book Experimental Evaluation of Expendable Supersonic Nozzle Concepts written by B. Vittal and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724326720 Total Pages :278 pages Book Rating :4.3/5 (267 download)
Book Synopsis Parametric Investigation of Single-Expansion-Ramp Nozzles at Mach Numbers from 0. 60 to 1. 20 by : National Aeronautics and Space Administration (NASA)
Download or read book Parametric Investigation of Single-Expansion-Ramp Nozzles at Mach Numbers from 0. 60 to 1. 20 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-27 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the effects of varying six nozzle geometric parameters on the internal and aeropropulsive performance characteristics of single-expansion-ramp nozzles. This investigation was conducted at Mach numbers from 0.60 to 1.20, nozzle pressure ratios from 1.5 to 12, and angles of attack of 0 deg +/- 6 deg. Maximum aeropropulsive performance at a particular Mach number was highly dependent on the operating nozzle pressure ratio. For example, as the nozzle upper ramp length or angle increased, some nozzles had higher performance at a Mach number of 0.90 because of the nozzle design pressure was the same as the operating pressure ratio. Thus, selection of the various nozzle geometric parameters should be based on the mission requirements of the aircraft. A combination of large upper ramp and large lower flap boattail angles produced greater nozzle drag coefficients at Mach number greater than 0.80, primarily from shock-induced separation on the lower flap of the nozzle. A static conditions, the convergent nozzle had high and nearly constant values of resultant thrust ratio over the entire range of nozzle pressure ratios tested. However, these nozzles had much lower aeropropulsive performance than the convergent-divergent nozzle at Mach number greater than 0.60. Capone, Francis J. and Re, Richard J. and Bare, E. Ann Langley Research Center NASA-TP-3240, L-17067, NAS 1.60:3240 RTOP 505-62-30-01...
Book Synopsis Fundamentals of Rocket Propulsion by : DP Mishra
Download or read book Fundamentals of Rocket Propulsion written by DP Mishra and published by CRC Press. This book was released on 2017-07-20 with total page 364 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book follows a unified approach to present the basic principles of rocket propulsion in concise and lucid form. This textbook comprises of ten chapters ranging from brief introduction and elements of rocket propulsion, aerothermodynamics to solid, liquid and hybrid propellant rocket engines with chapter on electrical propulsion. Worked out examples are also provided at the end of chapter for understanding uncertainty analysis. This book is designed and developed as an introductory text on the fundamental aspects of rocket propulsion for both undergraduate and graduate students. It is also aimed towards practicing engineers in the field of space engineering. This comprehensive guide also provides adequate problems for audience to understand intricate aspects of rocket propulsion enabling them to design and develop rocket engines for peaceful purposes.
Book Synopsis Facing the Heat Barrier by : T.A. Heppenheimer
Download or read book Facing the Heat Barrier written by T.A. Heppenheimer and published by Courier Dover Publications. This book was released on 2018-09-12 with total page 355 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Engineering the Space Age - a Rocket Scientist Remembers by : Robert Brulle
Download or read book Engineering the Space Age - a Rocket Scientist Remembers written by Robert Brulle and published by Createspace Independent Publishing Platform. This book was released on 2012-08 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Rarely is a reader exposed to such an extraordinary, multifaceted presentation of aerospace technology as Bob Brulle narrates in this book. After returning from duty as a combat fighter pilot in World War II, this Belgian immigrant developed a multitalented and innovative aerospace career path that addressed many of the aerospace professions. Along the way he forged a career in the aviation and space field that resulted in his participating in several of the most momentous aerospace achievements of the past century. He also expanded his education through hard work to a level at which he was qualified to teach graduate-level aerospace engineering courses. It is interesting to follow how the analysis and design techniques of aerospace vehicles progressed over the years, which incidentally reveals the large role that the computer played in making that possible. The story on the early Cape Canaveral operations was amusing and showed that enterprising innovations played a large role in a successful undertaking. Some of the projects described were a surprise, as I had never heard of them, like reading how a pencil-shaped missile was built that could fly and maneuver over an intercontinental distance at a high hypersonic velocity. He also described how American engineers and scientists fought the Cold War battle for technological supremacy on their desks and in their laboratories. The initiatives by which this enterprising engineer develops his technical approach to a project are very informative and offer the reader an insight into the workings of successful operations. He achieves an interesting behind-the-scenes look at how aerospace history is made by weaving in the historical significance of these projects as they are developed. As a former aeronautical engineer at the rapidly growing Mc- Donnell Aircraft Corporation, Bob gives us an interesting exposure to the importance of top management's relationship with the workforce in a successful company. "Mr. Mac" made it a point to make all his employees team members by frequent communication and friendly association.
Book Synopsis Aircraft Conceptual Design Synthesis by : Denis Howe
Download or read book Aircraft Conceptual Design Synthesis written by Denis Howe and published by . This book was released on 2000 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aircraft Conceptual Design Synthesis means design by fitness-for-purpose. Design engineers can jump off from the point of given parameters and requirements – required performance, payloads and other factors. This is the first book for the aeronautical designer devoted to guiding the reader through this highly effective conceptual design synthesis process. This forms the procedure for the initial stage of the aircraft design process – the interpretation of a requirement into the preliminary layout. A logical design sequence is developed utilizing original modules to represent propulsion, lift, drag, mass, and performance. Aircraft Conceptual Design Synthesis includes a disk of spreadsheets that provides core data. Unlike existing approaches, the design synthesis method can be applied to novel aircraft concepts. CONTENTS INCLUDE The design process Aircraft configuration Flight regime and powerplant considerations Fuselage layout Configuration of the wing Basic lift, drag and mass representations Performance estimation Parametric analysis and optimisation Analysis of concept design “This is an important landmark book and in my view will become a standard by which others will be compared” – Dr E C P Ransom, Kingston University, UK
Book Synopsis Understanding Aerospace Chemical Propulsion by : H. S. Mukunda
Download or read book Understanding Aerospace Chemical Propulsion written by H. S. Mukunda and published by . This book was released on 2017-02-28 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Explores aeronautical and space chemical propulsion. The book provides an understanding of propulsion systems through illustrative description of the systems; analysis of modeled systems; examination of the performance of real systems in this light; and a comparative assessment of aeronautical and space propulsion system elements.
