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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. -
Mp-Avt-146-29
UNCLASSIFIED/UNLIMITED Meeting Unmanned Air Vehicle Platform Challenges Using Oblique Wing Aircraft Dr. R.K. Nangia BSc, PhD, CEng, AFAIAA, FRAeS Consulting Engineers Nangia Aero Research Associates WestPoint, 78-Queens Road, BRISTOL, BS8 1QX UK [email protected] ABSTRACT There is an ever increasing emphasis on unmanned vehicles for all kinds of roles. Recent experience suggests that their capability and payoff could be complementary to manned vehicles in combat situations. However, the levels of platform and inter-disciplinary technologies need to be developed to take full advantage of their performance potential as part of an integrated defence system. This applies to all classes of Unmanned vehicles. Further, a balance has to be struck between manoeuvrability, stealth and enhancing range (persistence) whilst possibly combining reconnaissance and strike roles. A level of autonomy is implied (push button capability). Innovation and system integration is therefore called for. Future aircraft, particularly unmanned aircraft, will have substantially "widened" flight envelopes (higher "g", AoA and ß over wider Mach, altitude and CL ranges). An in depth analysis of aircraft weight breakdown (structure, fuel and payload) and the trends with time, size and technology levels, together with consideration and adaptation of the Breguet Range Equation has enabled derivation of Efficiency parameters leading to an appreciation of technologies needed for innovation and for further development. The paper focuses on the Oblique Flying Wing (OFW) concept to meet the goals of enhancing Range, Persistence whilst combining roles of Reconnaissance, Sensing and Strike. Several developing technologies, e.g. control, guidance and structure have prompted a “re-visit” to OFW. -
Experimental Investigation of Oblique Wing Aerodynamics at Low Speed
Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 3-2007 Experimental Investigation of Oblique Wing Aerodynamics at Low Speed Matthew J. Dillsaver Follow this and additional works at: https://scholar.afit.edu/etd Part of the Aerodynamics and Fluid Mechanics Commons Recommended Citation Dillsaver, Matthew J., "Experimental Investigation of Oblique Wing Aerodynamics at Low Speed" (2007). Theses and Dissertations. 2963. https://scholar.afit.edu/etd/2963 This Thesis is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. EXPERIMENTAL INVESTIGATION OF OBLIQUE WING AERODYNAMICS AT LOW SPEED THESIS Matthew J. Dillsaver, Captain, USAF AFIT/GAE/ENY/07-M10 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED The views expressed in this thesis are those of the author and do not reflect the official policy or position of the United States Air Force, Department of Defense, or the United States Government. AFIT/GAE/ENY/07-M10 EXPERIMENTAL INVESTIGATION OF OBLIQUE WING AERODYNAMICS AT LOW SPEED THESIS Presented to the Faculty Department of Aeronautics and Astronautics Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command In Partial Fulfillment of the Requirements for the Degree of Master of Science in Aeronautical Engineering Matthew J. Dillsaver, BSME Captain, USAF March 2007 APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED. -
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. -
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. -
Tools.Of.The.Trade+Poster.Pdf
Aircraft as Research Tools Aeronautical research usually begins with computers, wind The first experimental planes designed exclusively for re- tunnels, and flight simulators, but eventually the theories search were the XS-1 and the D-558-1. They were made in must fly. This is when flight research begins, and aircraft are 1946 to enable scientists and pilots to study flight near the the primary tools of the trade. speed of sound. Custom-made airplanes were the only means to accomplish this research because supersonic wind tun- Flight research involves doing precision maneuvers in ei- nels at the time were not accurate enough, and no other ther a specially built experimental aircraft or an existing pro- airplanes had flown that fast. The supersonic era began when duction airplane that has been modified. For example, the the XS-1 broke the “sound barrier” in 1947. AD-1 was a unique airplane made only for flight research, while the NASA F-18 High Alpha Research Vehicle (HARV) In the 1950’s the famous “X-Planes” continued to take people was a standard fighter aircraft that was transformed into a to higher altitudes and greater speeds. They were the first one-of-a-kind aircraft as it was fitted with new propulsion aircraft to fly Mach 2 and Mach 3, and the studies done with systems, flight controls, and scientific equipment. All research them influenced the designs of all supersonic planes. aircraft are able to perform scientific experiments because of the onboard instruments that record data about its sys- In the early 1960’s, the X-15 rocket plane became the first tems, aerodynamics, and the outside environment. -
Download Chapter 167KB
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. -
Library Copy
https://ntrs.nasa.gov/search.jsp?R=19840021778 2020-03-20T22:49:16+00:00Z A//_ 7"m-F_2 ._-F NASA Technical Memorandum 86258 NASA-TM-86258 19840021778 SOME AERODYNAMICDISCOVERIESAND RELATED NACAINASARESEARCHPROGRAMS FOLLOWING WORLD WAR II hi. LeroySpearman : June 1984 : LIBRARYCOPY AUG9 1984 LANGLEY RESEARCHCENTER LIBRARY, NASA _A_A HAMPTONV,IRGINIA National Aeronautics and Space Administration LangleyResearchCenter Hampton,Virginia23665 3 1176 00516 9314 SUMMARY Duringthe World War II time period, NACA test facilitieswere heavily committed to investigationsof airplanes related to the war effort. Much of the work was directed toward the improvementof existing airplanes but work was also being done on new designs. At one time in July 1944, 78 different models of airplanes were being investigated by NACA, most of them at the Langley Memorial Aeronautical Laboratory (now Langley ResearchCenter). Spin tests were made in the Langley spin tunnel on 120 different models. The atmospheric wind tunnel (AWT) tested 36 military aircraft for stability,control, and performancecharacteristics. In the post World War II period, an essentiallynew era of aerodynamicresearchbegan that was spawned by the lessons learned from air warfare and by some advances revealed from foreign technology,principallyin the developmentof jet propulsionand the advent of high-speedflight. INTRODUCTION In 1938, the growing menace of a military buildup in Germanywas obvious except to those who would not see it. President Roosevelt asked Congress for a major increasein defense appropriations,mostly for Naval strength,and got it. In early 1939, Roosevelt told Congress that U.S. air strength was "utterlyinadequate." At that time, the official strength included 1700 airplanes of which only 800 were considered first-line and these were primarily outdated Douglas B-18A's, Northrop A-17A's,and Curtiss P36A's. -
Morris' Wing.FM5
On the ’Wing... #117 Steve Morris’ Computer Stabilized Flying Wing Project In our December 1996 column, we included the following quote from Hans-Jürgen Unverferth of Germany: “Why do we use radio controls? To build constructions characterized by very high ‘own-stability’? It’s a joke! We have to be creative; fantasy has to rule our thoughts! Think about the F-16, B-2, all the modern fighters. There is no ‘own-stability,’ there is a computer! This is the future of model sailplaning. And there is one geometry waiting for this time — the tailless glider!”1 In July of 1987, at Dillon Beach California, an actively controlled unstable flying wing aircraft was successfully flown. This month’s column is devoted to an in-depth description of the aircraft and systems which made that success possible. The actively controlled unstable flying wing aircraft project was completed by Steve Morris (mentioned in a previous “On the ’Wing...” column), Rick Miley, and Dave Larkin, collectively called The Palo Alto Shipping Co., under the direction of Prof. Ilan Kroo of Stanford University and Dr. R.T. Jones. At the time of project inception, Steve had already been involved in the design, construction, and flying of a number of tailless RC models. He had written a rather sophisticated computer program to aid in the design process, and had, in fact, designed, built and flown a preliminary model of the S.W.I.F.T. (Swept Wing with Inboard Flap Trim) rigid wing hang glider.2 One problematic aspect of tailless flight which intrigued Steve can be directly related to “planks” and planforms with moderate rear sweep. -
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.