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Evolving the Oblique Wing
NASA AERONAUTICS BOOK SERIES A I 3 A 1 A 0 2 H D IS R T A O W RY T A Bruce I. Larrimer MANUSCRIP . Bruce I. Larrimer Library of Congress Cataloging-in-Publication Data Larrimer, Bruce I. Thinking obliquely : Robert T. Jones, the Oblique Wing, NASA's AD-1 Demonstrator, and its legacy / Bruce I. Larrimer. pages cm Includes bibliographical references. 1. Oblique wing airplanes--Research--United States--History--20th century. 2. Research aircraft--United States--History--20th century. 3. United States. National Aeronautics and Space Administration-- History--20th century. 4. Jones, Robert T. (Robert Thomas), 1910- 1999. I. Title. TL673.O23L37 2013 629.134'32--dc23 2013004084 Copyright © 2013 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks. Introduction v Chapter 1: American Genius: R.T. Jones’s Path to the Oblique Wing .......... ....1 Chapter 2: Evolving the Oblique Wing ............................................................ 41 Chapter 3: Design and Fabrication of the AD-1 Research Aircraft ................75 Chapter 4: Flight Testing and Evaluation of the AD-1 ................................... 101 Chapter 5: Beyond the AD-1: The F-8 Oblique Wing Research Aircraft ....... 143 Chapter 6: Subsequent Oblique-Wing Plans and Proposals ....................... 183 Appendices Appendix 1: Physical Characteristics of the Ames-Dryden AD-1 OWRA 215 Appendix 2: Detailed Description of the Ames-Dryden AD-1 OWRA 217 Appendix 3: Flight Log Summary for the Ames-Dryden AD-1 OWRA 221 Acknowledgments 230 Selected Bibliography 231 About the Author 247 Index 249 iii This time-lapse photograph shows three of the various sweep positions that the AD-1's unique oblique wing could assume. -
Supersonic Biplane Design Via Adjoint Method A
SUPERSONIC BIPLANE DESIGN VIA ADJOINT METHOD A DISSERTATION SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS AND THE COMMITTEE ON GRADUATE STUDIES OF STANFORD UNIVERSITY IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY Rui Hu May 2009 c Copyright by Rui Hu 2009 All Rights Reserved ii I certify that I have read this dissertation and that, in my opinion, it is fully adequate in scope and quality as a dissertation for the degree of Doctor of Philosophy. (Antony Jameson) Principal Adviser I certify that I have read this dissertation and that, in my opinion, it is fully adequate in scope and quality as a dissertation for the degree of Doctor of Philosophy. (Robert W. MacCormack) I certify that I have read this dissertation and that, in my opinion, it is fully adequate in scope and quality as a dissertation for the degree of Doctor of Philosophy. (Gianluca Iaccarino) Approved for the University Committee on Graduate Studies. iii Abstract In developing the next generation supersonic transport airplane, two major challenges must be resolved. The fuel efficiency must be significantly improved, and the sonic boom propagating to the ground must be dramatically reduced. Both of these objec- tives can be achieved by reducing the shockwaves formed in supersonic flight. The Busemann biplane is famous for using favorable shockwave interaction to achieve nearly shock-free supersonic flight at its design Mach number. Its performance at off-design Mach numbers, however, can be very poor. This dissertation studies the performance of supersonic biplane airfoils at design and off-design conditions. -
File:Thinking Obliquely.Pdf
NASA AERONAUTICS BOOK SERIES A I 3 A 1 A 0 2 H D IS R T A O W RY T A Bruce I. Larrimer MANUSCRIP . Bruce I. Larrimer Library of Congress Cataloging-in-Publication Data Larrimer, Bruce I. Thinking obliquely : Robert T. Jones, the Oblique Wing, NASA's AD-1 Demonstrator, and its legacy / Bruce I. Larrimer. pages cm Includes bibliographical references. 1. Oblique wing airplanes--Research--United States--History--20th century. 2. Research aircraft--United States--History--20th century. 3. United States. National Aeronautics and Space Administration-- History--20th century. 4. Jones, Robert T. (Robert Thomas), 1910- 1999. I. Title. TL673.O23L37 2013 629.134'32--dc23 2013004084 Copyright © 2013 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks. Introduction v Chapter 1: American Genius: R.T. Jones’s Path to the Oblique Wing .......... ....1 Chapter 2: Evolving the Oblique Wing ............................................................ 41 Chapter 3: Design and Fabrication of the AD-1 Research Aircraft ................75 Chapter 4: Flight Testing and Evaluation of the AD-1 ................................... 101 Chapter 5: Beyond the AD-1: The F-8 Oblique Wing Research Aircraft ....... 143 Chapter 6: Subsequent Oblique-Wing Plans and Proposals ....................... 183 Appendices Appendix 1: Physical Characteristics of the Ames-Dryden AD-1 OWRA 215 Appendix 2: Detailed Description of the Ames-Dryden AD-1 OWRA 217 Appendix 3: Flight Log Summary for the Ames-Dryden AD-1 OWRA 221 Acknowledgments 230 Selected Bibliography 231 About the Author 247 Index 249 iii This time-lapse photograph shows three of the various sweep positions that the AD-1's unique oblique wing could assume. -
Robert Jones
NATIONAL ACADEMY OF SCIENCES ROBERT THOMAS JONES 1910– 1999 A Biographical Memoir by WALTER G. VINCENTI Any opinions expressed in this memoir are those of the author and do not necessarily reflect the views of the National Academy of Sciences. Biographical Memoirs, VOLUME 86 PUBLISHED 2005 BY THE NATIONAL ACADEMIES PRESS WASHINGTON, D.C. ROBERT THOMAS JONES May 28, 1910–August 11, 1999 BY WALTER G. VINCENTI HE PLANFORM OF THE wing of every high-speed transport Tone sees flying overhead embodies R. T. Jones’s idea of sweepback for transonic and supersonic flight. This idea, of which Jones was one of two independent discoverers, was described by the late William Sears, a distinguished aerody- namicist who was a member of the National Academy of Sciences, as “certainly one of the most important discover- ies in the history of aerodynamics.” It and other achieve- ments qualify him as among the premier theoretical aero- dynamicists of the twentieth century. And this by a remarkable man whose only college degree was an honorary doctorate. Robert Thomas Jones––“R.T.” to those of us fortunate enough to be his friend––was born on May 28, 1910, in the farming-country town of Macon, Missouri, and died on Au- gust 11, 1999, at age 89, at his home in Los Altos Hills, California. His immigrant grandfather, Robert N. Jones, af- ter being in the gold rush to California, settled near Ma- con, where he farmed in the summer and mined coal in the winter. His father, Edward S. Jones, educated himself in the law and practiced law in Macon; while running for pub- lic office, he traveled the dirt roads of Macon county in a buggy behind a single horse. -
Birth of Sweepback: Related Research at Luftfahrtforschungsanstalt—Germany
JOURNAL OF AIRCRAFT Vol. 42, No. 4, July–August 2005 History of Key Technologies Birth of Sweepback: Related Research at Luftfahrtforschungsanstalt—Germany Peter G. Hamel∗ Technical University Braunschweig, D-38092 Braunschweig, Germany “Be more attentive to new ideas from the research world.” George S. Schairer, former Vice President Research, Boeing (1989) An extended historical review is given about German World War II scientific and industrial research on the beneficial effects of wing sweep on aircraft design by reducing transonic drag rise. The specific role of the former Luftfahrtforschungsanstalt (LFA), which was located in Braunschweig-Voelkenrode, is emphasized. Reference is given to LFA’s partner research organization Aerodynamische Versuchsanstalt in Goettingen, the scientific birthplace of modern aerodynamics. Wind-tunnel facilities at LFA, which were taken out of existence after World War II, are illustrated. Advanced missile research and aircraft support projects at LFA are illuminated. Further, the postwar technical know-how transfer and its implementation to U.S. and other international aircraft projects is highlighted together with contributions of some former German researchers to the advances of aeronautics. Introduction and Beginnings cists at the Aerodynamische Versuchsanstalt (AVA) in Goettingen, OOKING back over the 110 years that have passed since who established systematic wind-tunnel tests to generate a world- first database for future transonic aircraft configurations with wing L the Otto Lilienthal brothers’ aerodynamic model experiments , 7 12 yielded the world’s first manned glider flights at Berlin-Lichterfelde sweep (Figs. 2a and 2b). (1891), and reflecting the first centenary since the Wright brothers’ Complementary swept-wing model wind-tunnel tests were suc- wind-tunnel model tests resulted in the historic manned powered cessively accomplished at Luftfahrtforschungsanstalt (LFA) in flights at Kitty Hawk (1903), we also recall that there was another im- Braunschweig-Voelkenrode (Fig. -
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Memorial Tributes: Volume 3 ADOLF BUSEMANN 62 Copyright National Academy of Sciences. All rights reserved. Memorial Tributes: Volume 3 ADOLF BUSEMANN 63 Adolf Busemann 1901–1986 By Robert T. Jones Adolf Busemann, an eminent scientist and world leader in supersonic aerodynamics who was elected to the National Academy of Engineering in 1970, died in Boulder, Colorado, on November 3, 1986, at the age of eighty-five. At the time of his death, Dr. Busemann was a retired professor of aeronautics and space science at the University of Colorado in Boulder. Busemann belonged to the famous German school of aerodynamicists led by Ludwig Prandtl, a group that included Theodore von Karman, Max M. Munk, and Jakob Ackeret. Busemann was the first, however, to propose the use of swept wings to overcome the problems of transonic and supersonic flight and the first to propose a drag-free system of wings subsequently known as the Busemann Biplane. His ''Schock Polar,'' a construction he described as a "baby hedgehog," has simplified the calculations of aerodynamicists for decades. Adolf Busemann was born in Luebeck, Germany, on April 20, 1901. He attended the Carolo Wilhelmina Technical University in Braunschweig and received his Ph.D. in engineering there in 1924. In 1930 he was accorded the status of professor (Venia Legendi) at Georgia Augusta University in Goettingen. In 1925 the Max-Planck Institute appointed him to the position of aeronautical research scientist. He subsequently Copyright National Academy of Sciences. All rights reserved. Memorial Tributes: Volume 3 ADOLF BUSEMANN 64 held several positions in the German scientific community, and during the war years, directed research at the Braunschweig Laboratory. -
Aerial Metamorphosis:Metamorphosis: Variablevariable Sweepsweep Wingswings 1
AerialAerial Metamorphosis:Metamorphosis: VariableVariable SweepSweep WingsWings 1 Brian Hayes Eugene Heim AOE 4124 OutlineOutline TheThe Jet Jet Age Age Aerodynamic Lift At Supersonic Speed Increasing Critical Mach Number In-FlightIn-Flight Optimization Optimization Pivoting Around Stall Variable Sweep – Variable Mission VariableVariable Sweep Sweep Aircraft Aircraft Variable Sweep Wings AOE 4124 2 TheThe Jet Jet Age Age 3 Advances in propulsion in 1930’s made sustained high- subsonic, transonic, and supersonic flight possible High-speed WWII era aircraft typically had strait wings and http://www.acepilots.com/planes/p51_mustang.html thickness ratios of 14 to 18 http://www.acepilots.com/planes/p38_lightning.html percent Variable Sweep Wings AOE 4124 3 AerodynamicAerodynamic LiftLift AtAt SupersonicSupersonic SpeedSpeed2 1935 Adolf Busemann, Aviation Research Organization, Germany 1941 Michael Gluhareff, Sikorsky chief of design 1945 Robert T. Jones, NACA Langley aerodynamicist http://www.hiller.org/about-us/briefings-journal/briefings/2000q4.pdf Variable Sweep Wings AOE 4124 4 IncreasingIncreasing Critical Critical Mach Mach Number Number http://www.eng.vt.edu/fluids/msc/gallery/shocks/p25b.htm 1 Independence of velocity components is true only for invisid flow Overestimates Mcr,L Variable Sweep Wings AOE 4124 5 ThicknessThickness RatioRatio andand SweepSweep AngleAngle 1 Variable Sweep Wings AOE 4124 6 ProblemsProblems At At Stall Stall Serious S&C problems at high a near stall NACA Bell L-39 swept wing flight study 1 Variable Sweep -
Induced Drag and High-Speed Aerodynamics
Induced Drag and High-Speed Aerodynamics Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2018 • Drag-due-to-lift and effects of wing planform • Effect of angle of attack on lift and drag coefficients • Mach number (i.e., air compressibility) effects on aerodynamics • Newtonian approximation for lift and drag Reading: Flight Dynamics Aerodynamic Coefficients, 85-96 Airplane Stability and Control Chapter 1 Copyright 2018 by Robert Stengel. All rights reserved. For educational use only. http://www.princeton.edu/~stengel/MAE331.html http://www.princeton.edu/~stengel/FlightDynamics.html 1 Induced Drag 2 1 Aerodynamic Drag 1 1 Drag = C ρV 2S ≈ C + εC 2 ρV 2S D 2 ( D0 L ) 2 2 1 ≈ ⎡C + ε C + C α ⎤ ρV 2S ⎣⎢ D0 ( Lo Lα ) ⎦⎥ 2 3 2 Induced Drag of a Wing, εCL § Lift produces downwash (angle proportional to lift) § Downwash rotates local velocity vector clockwise in figure § Lift is perpendicular to velocity vector § Axial component of rotated lift induces drag § But what is the proportionality factor, ε? 4 2 Induced Angle of Attack C C sin , where Di = L α i α i = CL πeAR, Induced angle of attack C = C sin C πeAR C 2 πeAR Di L ( L ) ! L 5 Three Expressions for Induced Drag of a Wing C 2 C 2 1+δ C L L ( ) C 2 Di = ! ! ε L πeAR π AR e = Oswald efficiency factor = 1 for elliptical distribution δ = departure from ideal elliptical lift distribution 1 (1+δ ) ε = = πeAR π AR 6 3 Spanwise Lift Distribution of Elliptical and Trapezoidal Wings Straight Wings (@ 1/4 chord), McCormick Spitfire TR = taper ratio, λ P-51D Mustang For some taper ratio between 0.35 and 1, trapezoidal lift distribution is nearly elliptical 7 Induced Drag Factor, δ 2 CL (1+ δ ) C = Di π AR • Graph for δ (McCormick, p. -
Schnellflug- Und Pfeilflügeltechnik
Der weitere Rundgang in der Halle 2 - die Schnellflugausstellung und die Geschichte der aerodynamischen Pfeilflügeltechnik mit der durch sie veränderten Welt Bevor wir Sie weiter durch unsere Ausstellung führen, wollen wir Sie ein wenig über die Hintergründe unserer Arbeit vertraut machen. Wir benötigen dafür Fachwissen mit breitem Hintergrund, und das müssen wir zusammen- tragen. Im Lauf der letzten 25 Jahre ist das eine stattliche Menge geworden und wird in unserem Archiv in einem Nebengebäude bearbeitet und verwaltet. Selbstverständlich müssen schon Grundkenntnisse durch eine längere Beschäftigung mit diesem komplexen Thema vorhanden sein, seien es technische, historische oder noch andere Zugänge. Unser Archiv: Oben links die Büchersammlung, rechts ebenso mit einem Teil der Flugzeug- Typensammlung, unten die Buchstaben A - D der Typensammlung in den A4-Ordnern. Doch kann man sich auch als Fachfremder gut darin einarbeiten, wenn man "zur Stange" hält. Wir alle sind als ehrenamtliche Mitarbeiter im Museumsteam keine studierten Museums- pädagogen oder sonstige Fachwissenschaftler, sondern Menschen aus allen möglichen Berufen, Handwerker und Juristen, Verwaltungsleute und Mediziner. Uns eint die Liebe zur Fliegerei, deren Technik und der Wille zur historischen Einordnung. Und ordentlich mit solchen Themen umzugehen, haben wir in anderen Berufen gelernt. Im Archivgebäude haben wir mehrere Räume, in denen einmal so um 4 - 5 tausend Bücher, diverse Luftfahrtzeitschriften und andere Periodika versammelt sind. Dazu kommt eine ausgedehnte Flugzeugtypensammlung, die sich aus Veröffentlichungen einheimischer und auswärtiger Luftfahrtzeitschriften über die letzen 60 - 70 Jahre speist, mit Motor-, Segel- und UL-Flugzeugen sowie Hubschraubern. Das sind noch einmal gute 800 A-4 Bände, Die verschiedenen Typen sind nach Herstellern alphabetisch sortiert. Dieses Archiv dürfen Sie nach tel. -
Quieting the Boom : the Shaped Sonic Boom Demonstrator and the Quest for Quiet Supersonic Flight / Lawrence R
Lawrence R. Benson Lawrence R. Benson Library of Congress Cataloging-in-Publication Data Benson, Lawrence R. Quieting the boom : the shaped sonic boom demonstrator and the quest for quiet supersonic flight / Lawrence R. Benson. pages cm Includes bibliographical references and index. 1. Sonic boom--Research--United States--History. 2. Noise control-- Research--United States--History. 3. Supersonic planes--Research--United States--History. 4. High-speed aeronautics--Research--United States-- History. 5. Aerodynamics, Supersonic--Research--United States--History. I. Title. TL574.S55B36 2013 629.132’304--dc23 2013004829 Copyright © 2013 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks. ISBN 978-1-62683-004-2 90000> 9 781626 830042 Preface and Acknowledgments v Introduction: A Pelican Flies Cross Country ix Chapter 1: Making Shock Waves: The Proliferation and Testing of Sonic Booms ............................. 1 Exceeding Mach 1 A Swelling Drumbeat of Sonic Booms Preparing for an American Supersonic Transport Early Flight Testing Enter the Valkyrie and the Blackbird The National Sonic Boom Evaluation Last of the Flight Tests Chapter 2: The SST’s Sonic Boom Legacy ..................................................... 39 Wind Tunnel Experimentation Mobilizing -
Plasma Aerodynamics Since the End of the Cold War Dennis C
Florida State University Libraries Electronic Theses, Treatises and Dissertations The Graduate School 2012 Plasma Aerodynamics since the End of the Cold War Dennis C. Mills Follow this and additional works at the FSU Digital Library. For more information, please contact [email protected] THE FLORIDA STATE UNIVERSITY COLLEGE OF ARTS AND SCIENCES PLASMA AERODYNAMICS SINCE THE END OF THE COLD WAR By DENNIS C. MILLS A Dissertation submitted to the Department of History in partial fulfillment of the requirements for the degree of Doctor of Philosophy Degree Awarded: Summer Semester, 2012 Dennis C. Mills defended this dissertation on April 19, 2012. The members of the supervisory committee were: Jonathan Grant Professor Directing Dissertation Michael Ruse University Representative Frederick Davis Committee Member Edward Wynot Committee Member Rafe Blaufarb Committee Member The Graduate School has verified and approved the above-named committee members, and certifies that the dissertation has been approved in accordance with university requirements. ii To my mother and my wife. iii ACKNOWLEDGEMENTS This journey began back in junior high school around 1970 when I first realized I enjoyed history. Many people helped along the way and I truly wish I could personally thank each and every one of them for the achievement of a life-long dream. They assisted in this long journey and I am forever in their gratitude. iv TABLE OF CONTENTS ABSTRACT .................................................................................................................................. -
Reflections on Applied Computational Aerodynamics (ACA) My Journey on a Long and Winding Road in the Quest for Fully Effective ACA—A Bridge Too Far!
Reflections on Applied Computational Aerodynamics (ACA) My Journey on a Long and Winding Road in the Quest for Fully Effective ACA—A Bridge Too Far! Pradeep Raj, Ph.D. Professor, Kevin T. Crofton Department of Aerospace and Ocean Engineering Virginia Tech, Blacksburg, Virginia, USA http://www.aoe.vt.edu/people/faculty/raj.html Program Management Director, Lockheed Martin (Retired) Deputy Director, Technology Development & Integration The Skunk Works®, Palmdale, California, USA Fully Effective ACA ≡ ACA Nirvana*! 07 July 2021 (*a goal hoped for but apparently unattainable) 1 Copyright © 2021 by Pradeep Raj. All Rights Reserved. About the Author Pradeep Raj • Virginia Tech, Blacksburg, VA – Professor (2012 - present) o Teaching: AOE Air Vehicle Design and ACA o Research: Applied Aerodynamics for Aircraft Design • Lockheed Martin (Retd.) – Prog. Mgmt. Director (2011) The Skunk Works®, Aeronautics Co., Palmdale, California • Lockheed, Burbank – Sr. Aero. Engineer (1979) • UMR*, Rolla, Missouri – Asst. Prof. (1978) • ISU, Ames, Iowa – Res. Asst. Prof. (1976) • GT, Atlanta, Georgia – Ph.D. Aerospace Engineering (1976) • IISc, Bangalore, India – B.E. Elec. Tech. (1970) – M.E. Aero. Engr. (1972) • Fellow of AIAA, RAeS, and IAE Image Source: Internet 2 *now Missouri S&T University Copyright © 2021 by Pradeep Raj. All Rights Reserved. Why Raj Joined VT After Retirement from LM? Clarence Leonard “Kelly” Johnson (1910-1990) Legendary Aircraft Designer Founder of World-renowned Skunk Works® “Hang with young people; they mostly have it right” 3 Copyright © 2021 by Pradeep Raj. All Rights Reserved. About This Presentation This is a revised, updated, and much expanded version of the Lead Presentation: Applied Computational Aerodynamics: An Unending Quest for Effectiveness presented at the Royal Aeronautical Society Applied Aerodynamics Conference— The Future of Aerodynamics, Bristol, U.K., July 24-26, 2018.