Download or read book Aerodynamics Aeronautics and Flight Mechanics written by Barnes W. McCormick and published by John Wiley & Sons. This book was released on 1994-09-28 with total page 677 pages. Available in PDF, EPUB and Kindle. Book excerpt: A New Edition of the Most Effective Text/Reference in the Field! Aerodynamics, Aeronautics, and Flight Mechanics, Second Edition Barnes W. McCormick, Pennsylvania State University 57506-2 When the first edition of Aerodynamics, Aeronautics, and Flight Mechanics was published, it quickly became one of the most important teaching and reference tools in the field. Not only did generations of students learn from it, they continue to use it on the job-the first edition remains one of the most well-thumbed guides you'll find in an airplane company. Now this classic text/reference is available in a bold new edition. All new material and the interweaving of the computer throughout make the Second Edition even more practical and current than before! A New Edition as Complete and Applied as the First Both analytical and applied in nature, Aerodynamics, Aeronautics, and Flight Mechanics presents all necessary derivations to understand basic principles and then applies this material to specific examples. You'll find complete coverage of the full range of topics, from aerodynamics to propulsion to performance to stability and control. Plus, the new Second Edition boasts the same careful integration of concepts that was an acclaimed feature of the previous edition. For example, Chapters 9, 10, and 11 give a fully integrated presentation of static, dynamic, and automatic stability and control. These three chapters form the basis of a complete course on stability and control. New Features You'll Find in the Second Edition * A new chapter on helicopter and V/STOL aircraft- introduces a phase of aerodynamics not covered in most current texts * Even more material than the previous edition, including coverage of stealth airplanes and delta wings * Extensive use of the computer throughout- each chapter now contains several computer exercises * A computer disk with programs written by the author is available

Download or read book Annual Report for the Fiscal Year written by National Library of Medicine (U.S.) and published by . This book was released on 1959 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Twisting Effect at Transonic Speeds of Spoiler Ailerons on a 45 Sweptback Aspect ratio 4 Tapered Wing written by Alexander D. Hammond and published by . This book was released on 1954 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1918 with total page 570 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Robert F. Thompson and published by . This book was released on 1950 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.

Download or read book Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45 Swept wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail written by M. Leroy Spearman and published by . This book was released on 1957 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.

Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3 a Taper Ratio of 0 2 and NACA 65A004 Airfoil Sections written by Jack F. Runckel and published by . This book was released on 1956 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.

Download or read book The Aerodynamic Design of Aircraft written by Dietrich Küchemann and published by AIAA Education. This book was released on 2012 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Dietrich Kuchemann's The Aerodynamic Design of Aircraft is as relevant and as forward looking today as it was when it was first published in 1978. It comprises the philosophy and life's work of a unique and visionary intellect. Based upon material taught in a course at Imperial College London, the insight and intuition conveyed by this text are timeless. With its republication, Kuchemann's influence will extend to the next generation of aerospace industry students and practitioners and the vehicles they will produce. Kuchemann establishes three classes of aircraft based on the character of flow involved. Each class is suitable for a distinct cruise speed regime: classical and swept aircraft for subsonic and transonic cruise, slender-wing aircraft for supersonic cruise, and wave-rider aircraft for hypersonic cruise. Unlike most engineering texts, which focus on a set of tools, Kuchemann's approach is to focus on the problem and its solution - what kind of flow is best for a given class of aircraft and how to achieve it.With this approach, Kuchemann fully embraces the true inverse nature of design; rather than answer what flow given the shape, he strives to answer what flow given the purpose and then what shape given the flow.

Download or read book Aerodynamics of V STOL Flight written by Barnes Warnock McCormick and published by Courier Corporation. This book was released on 1999-01-01 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extremely practical overview of V/STOL (vertical/short takeoff and landing) aerodynamics, this volume offers a presentation of general theoretical and applied aerodynamic principles, covering propeller and helicopter rotor theory for both the static and forward flight cases. Both a text for students and a reference for professionals, the book can be used for advanced undergraduate or graduate courses. Numerous detailed figures, plus exercises. 1967 edition. Preface. Appendix. Index.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation at Transonic Speeds of Loading Over a 30 Deg Sweptback Wing of Aspect Ratio 3 Taper Ratio 0 2 and NACA 65A004 Airfoil Section Mounted on a Body written by Donald D. Arabian and published by . This book was released on 1960 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic load characteristics of a wing-body combination were determined experimentally at Mach numbers from 0.80 to 1.03 for angles of attack up to 26 degrees. Two wings, both with 30 degrees sweep of the quarter-chord line, taper ratio of 0.2, aspect ratio of 3, and thickness of 4 percent chord, but of different types of construction, were tested. One wing was of solid steel and the other was of plastic with an inner steel core ...

Download or read book Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0 40 to 0 93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.

Download or read book Free flight Measurements of the Rolling Effectiveness and Drag of Trailing edge Spoilers on a Tapered Sweptback Wing at Mach Numbers Between 0 6 and 1 4 written by Eugene D. Schult and published by . This book was released on 1954 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Rolling Moment Due to Sideslip of Swept Wings at Subsonic and Transonic Speeds written by Edward C. Polhamus and published by . This book was released on 1955 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A summary and analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip characteristics of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range.

Download or read book Wing Theory written by Robert Thomas Jones and published by Princeton University Press. This book was released on 2014-07-14 with total page 227 pages. Available in PDF, EPUB and Kindle. Book excerpt: Originator of many of the theories used in modern wing design, Robert T. Jones surveys the aerodynamics of wings from the early theories of lift to modern theoretical developments. This work covers the behavior of wings at both low and high speeds, including the range from very low Reynolds numbers to the determination of minimum drag at supersonic speed. Emphasizing analytical techniques, Wing Theory provides invaluable physical principles and insights for advanced students, professors, and aeronautical engineers, as well as for scientists involved in computational approaches to the subject. This book is based on over forty years of theoretical and practical work performed by the author and other leading researchers in the field of aerodynamics. Originally published in 1990. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.

Download or read book Aerodynamic Characteristics of a Spoiler slot deflector Control on a 45 Sweptback Wing at Mach Numbers of 1 61 and 2 01 written by Douglas R. Lord and published by . This book was released on 1957 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.

Download or read book Preliminary Results of the Flight Investigation Between Mach Numbers of 0 80 and 1 36 of a Rocket powered Model of a Supersonic Airplane Configuration Having a Tapered Wing with Circular arc Sections and 40 Sweepback written by Charles T. D'Aiutolo and published by . This book was released on 1950 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: