Aerodynamic of Sonic Flight
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Years Years Service Or 20,000 Hours of Flying
VOL. 9 NO. 1 OCTOBER 2001 MAGAZINE OF THE ASSOCIATION OF ASIA PACIFIC AIRLINES 50 50YEARSYEARS Japan Airlines celebrating a golden anniversary AnsettAnsett R.I.PR.I.P.?.? Asia-PacificAsia-Pacific FleetFleet CensusCensus UPDAUPDATETE U.S.U.S. terrterroror attacks:attacks: heavyheavy economiceconomic fall-outfall-out forfor Asia’Asia’ss airlinesairlines VOL. 9 NO. 1 OCTOBER 2001 COVER STORY N E W S Politics still rules at Thai Airways International 8 50 China Airlines clinches historic cross strait deal 8 Court rules 1998 PAL pilots’ strike illegal 8 YEARS Page 24 Singapore Airlines pulls out of Air India bid 10 Air NZ suffers largest corporate loss in New Zealand history 12 Japan Airlines’ Ansett R.I.P.? Is there any way back? 22 golden anniversary Real-time IFE race hots up 32 M A I N S T O R Y VOL. 9 NO. 1 OCTOBER 2001 Heavy economic fall-out for Asian carriers after U.S. terror attacks 16 MAGAZINE OF THE ASSOCIATION OF ASIA PACIFIC AIRLINES HELICOPTERS 50 Flying in the face of bureaucracy 34 50YEARS Japan Airlines celebrating a FEATURE golden anniversary Training Cathay Pacific Airways’ captains of tomorrow 36 Ansett R.I.P.?.? Asia-Pacific Fleet Census UPDATE S P E C I A L R E P O R T Asia-Pacific Fleet Census UPDATE 40 U.S. terror attacks: heavy economic fall-out for Asia’s airlines Photo: Mark Wagner/aviation-images.com C O M M E N T Turbulence by Tom Ballantyne 58 R E G U L A R F E A T U R E S Publisher’s Letter 5 Perspective 6 Business Digest 51 PUBLISHER Wilson Press Ltd Photographers South East Asia Association of Asia Pacific Airlines GPO Box 11435 Hong Kong Andrew Hunt (chief photographer), Tankayhui Media Secretariat Tel: Editorial (852) 2893 3676 Rob Finlayson, Hiro Murai Tan Kay Hui Suite 9.01, 9/F, Tel: (65) 9790 6090 Kompleks Antarabangsa, Fax: Editorial (852) 2892 2846 Design & Production Fax: (65) 299 2262 Jalan Sultan Ismail, E-mail: [email protected] Ü Design + Production Web Site: www.orientaviation.com E-mail: [email protected] 50250 Kuala Lumpur, Malaysia. -
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. -
A PERSONAL VIEW by Dr Ken Ramsden 2010
THE PAST PRESENT AND FUTURE WITH AIRCRAFT AND THEIR ENGINES A PERSONAL VIEW BY Dr Ken Ramsden 2010 1 CONTENTS HISTORY OF FLIGHT EARLY COMMERCIAL AVIATION COMPETITION CURRENT TECHNOLOGY OF CIVIL AIRCRAFT THE NEAR FUTURE WITH CIVIL AIRCRAFT THE LONG TERM FUTURE FOR CIVIL AIRCRAFT?? HISTORICAL DEVELOPMENT OF AIRCRAFT ENGINES CURRENT AIRCRAFT ENGINES FUTURE ENGINE DEVELOPMENT MODERN MILITARY AIRCRAFT AND ENGINES 2 HISTORY OF FLIGHT 1903 Wright Brothers – First Powered Flight - Kittyhawk OR SANTOS DUMONT 1947 Chuck Yeager Sound Barrier X-1 1961 Yurij Gagarin – Space Flight 3 HISTORY OF FLIGHT THE THIRTIES AND FORTIES BATTLE OF BRITAIN FLIGHT SUPERMARINE SPITFIRE AVRO LANCASTER HAWKER HURRICANE 4 HISTORY OF FLIGHT THE FIFTIES AND SIXTIES THE AVIATION MONOPOLY RACE BLIGHTED BY POLITICS TSR2 Mach 0.9 at sea level Mach 2.2 at 60000 ft Commercially unsuccessful ?? CONCORDE – MACH 2 AT 60000 FT “OLYMPIC ENGINES” FF IN MARCH 69, LAUNCHED IN 1976 5 HISTORY OF FLIGHT TSR2 AND (FLYING) VULCAN AT DUXFORD TSR 2 - XR222 6 EARLY COMMERCIAL AVIATION COMPETITION 7 EARLY COMMERCIAL AVIATION COMPETITION TECHNICALLY UNSUCCESSFUL ?? COMET - Mach 0.85 AT 36000 FT SQUARE WINDOWS FF JULY 49 WITH HIGH CORNER STRESS LAUNCHED JAN 52 Ken’s theory DeH GHOST ENGINES LOW FREQUENCY PISTON ENGINES WITHDRAWN EARLY 80’s VERSUS HIGH FREQUENCY GT’S ?? 8 EARLY COMMERCIAL AVIATION COMPETITION COMMERCIALLY SUCCESSFUL BOEING 707 FF JULY 54 LAUNCHED OCT 58 ENGINES JT3D OR CFM56 BOEING 737 FF APRIL 67 LAUNCHED FEB 68 ENGINES JT8D OR CFM56 9 CURRENT TECHNOLOGY OF CIVIL AIRCRAFT 10 CURRENT -
7. Transonic Aerodynamics of Airfoils and Wings
W.H. Mason 7. Transonic Aerodynamics of Airfoils and Wings 7.1 Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = 0.6 or 0.7 to 1.2). Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds. This complicates both computations and wind tunnel testing. It also means that there is very little analytic theory available for guidance in designing for transonic flow conditions. Importantly, not only is the outer inviscid portion of the flow governed by nonlinear flow equations, but the nonlinear flow features typically require that viscous effects be included immediately in the flowfield analysis for accurate design and analysis work. Note also that hypersonic vehicles with bow shocks necessarily have a region of subsonic flow behind the shock, so there is an element of transonic flow on those vehicles too. In the days of propeller airplanes the transonic flow limitations on the propeller mostly kept airplanes from flying fast enough to encounter transonic flow over the rest of the airplane. Here the propeller was moving much faster than the airplane, and adverse transonic aerodynamic problems appeared on the prop first, limiting the speed and thus transonic flow problems over the rest of the aircraft. However, WWII fighters could reach transonic speeds in a dive, and major problems often arose. One notable example was the Lockheed P-38 Lightning. Transonic effects prevented the airplane from readily recovering from dives, and during one flight test, Lockheed test pilot Ralph Virden had a fatal accident. -
Airlines and Tourism Development: the Case of Zimbabwe 69 Brian Turton
TOURISM AND TRANSPORT ISSUES AND AGENDA FOR THE NEW MILLENNIUM ADVANCES IN TOURISM RESEARCH Series Editor: Professor Stephen J. Page University of Stirling, U.K. [email protected] Advances in Tourism Research series publishes monographs and edited volumes that comprise state-of-the-art research findings, written and edited by leading researchers working in the wider field of tourism studies. The series has been designed to provide a cutting edge focus for researchers interested in tourism, particularly the management issues now facing decision makers, policy analysts and the public sector. The audience is much wider than just academics and each book seeks to make a significant contribution to the literature in the field of study by not only reviewing the state of knowledge relating to each topic but also questioning some of the prevailing assumptions and research paradigms which currently exist in tourism research. The series also aims to provide a platform for further studies in each area by highlighting key research agendas which will stimulate further debate and interest in the expanding area of tourism research. The series is always willing to consider new ideas for innovative and scholarly books, inquiries should be made directly to the Series Editor. Published: THOMAS Small Firms in Tourism: International Perspectives KERR Tourism Public Policy and the Strategic Management of Failure WILKS & PAGE Managing Tourist Health and Safety in the New Millennium BAUM & LUNDTORP Seasonality in Tourism ASHWORTH & TUNBRIDGE The Tourist-Historic -
New Trends in Future Aircraft Development
NEW TRENDS IN FUTURE AIRCRAFT DEVELOPMENT S. Tsach and D. Penn Engineering Division Israel Aircraft Industries (IAI) Ben-Gurion Airport, Israel ABSTRACT This paper reviews the new trends that are emerging in the development of air vehicles of the future. Technological developments in many fields are reviewed, including aerodynamics, propulsion, flight control, structures, materials, production techniques, avionics, communications, computerization, miniaturization and others. The paper addresses the future needs and requirements of both the military and civil aerospace markets. The needs of military intelligence are expressed in the considerable progress made in the development of UAVs. The transportation needs of passengers and cargo are expressed in the continuous search for greater efficiency and cost reduction in an ever-expanding market place. The review includes examples of developments in the field of civilian aircraft such as Airbus 380, Sonic Cruiser, BWB configuration and supersonic business jet; and discusses technological developments in small business aircraft like the Eclipse 500 and the SATS programs of NASA. Developments in the sphere of unmanned aircraft are described, including UCAVs, OAV, CRW, solar HALE, micro-UAVs and also sensor craft goals are addressed. The paper examines the technological goals which industry has defined for the improvement of aviation and air vehicles, highlighting the American and European long term plans as published in the American Aerospace Commission report, “NASA Aeronautics Blueprint” and the European document “ARTE21”. Some examples of IAI’s recent activities in aircraft development and the integration of advanced technologies are described. This includes the use of CFD for design and improvement of advanced aircraft and the use of production techniques for composite materials with reference to the G150, Airtruck and the family of Heron UAVs. -
Section 7, Lecture 3: Effects of Wing Sweep
Section 7, Lecture 3: Effects of Wing Sweep • All modern high-speed aircraft have swept wings: WHY? 1 MAE 5420 - Compressible Fluid Flow • Not in Anderson Supersonic Airfoils (revisited) • Normal Shock wave formed off the front of a blunt leading g=1.1 causes significant drag Detached shock waveg=1.3 Localized normal shock wave Credit: Selkirk College Professional Aviation Program 2 MAE 5420 - Compressible Fluid Flow Supersonic Airfoils (revisited, 2) • To eliminate this leading edge drag caused by detached bow wave Supersonic wings are typically quite sharp atg=1.1 the leading edge • Design feature allows oblique wave to attachg=1.3 to the leading edge eliminating the area of high pressure ahead of the wing. • Double wedge or “diamond” Airfoil section Credit: Selkirk College Professional Aviation Program 3 MAE 5420 - Compressible Fluid Flow Wing Design 101 • Subsonic Wing in Subsonic Flow • Subsonic Wing in Supersonic Flow • Supersonic Wing in Subsonic Flow A conundrum! • Supersonic Wing in Supersonic Flow • Wings that work well sub-sonically generally don’t work well supersonically, and vice-versa à Leading edge Wing-sweep can overcome problem with poor performance of sharp leading edge wing in subsonic flight. 4 MAE 5420 - Compressible Fluid Flow Wing Design 101 (2) • Compromise High-Sweep Delta design generates lift at low speeds • Highly-Swept Delta-Wing design … by increasing the angle-of-attack, works “pretty well” in both flow regimes but also has sufficient sweepback and slenderness to perform very Supersonic Subsonic efficiently at high speeds. • On a traditional aircraft wing a trailing vortex is formed only at the wing tips. -
Naca Research Memorandum
RM No. L8A28c NACA RESEARCH MEMORANDUM EFFECTS OF SWEEP ON CONTROLS By John G. Lowry, John A. Axelson, and Harold I. Johnson Langley Memorial Aeronautical La 00 ratory Langley Field, Va. NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON June 3, 1948 Declassified February 10, 1956 NACA PM No. L8A28c NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS RESEARCH MEMORANDUM EFFECTS OF SWEEP ON CONTROLS By John G. Lowry., John A. Axelson, and Harold I. Johnson SUMMARY An analysis of principal results of recent control-surface research pertinent to transonic flight has -been made. Available experimental data on control surfaces of both unswept and sweptback configurations at transonic speeds are used to indiäate the control-surface characteristics in the transonic speed range. A design procedure for controls on swept- back wings based on low-speed experimental data is also discussed. The results indicated, that no serious problems resulting from compressibility effects would be encountered as long as the speeds are kept below the critical speed of the wing and the trailing-edge angle is kept small. Above critical speed, however, the behavior of the' controls depended to a large extent on the wing sweep angle. The design procedures presented for controls on swept wings, although of a preliminary nature, appear to offer a method of estimating the effec- tiveness of flap-type controls on swept wings of normal aspect ratio and taper ratio. INTRODUCTION The design of controls for unswept wings that fly at low speed has been discussed in several papers (references 1 to 7). The design procedures set forth in these papers are adequate to allow for the prediction of control characteristics within small limits. -
Air Travel, Life-Style, Energy Use and Environmental Impact
Air travel, life-style, energy use and environmental impact Stefan Kruger Nielsen Ph.D. dissertation September 2001 Financed by the Danish Energy Agency’s Energy Research Programme Department of Civil Engineering Technical University of Denmark Building 118 DK-2800 Kgs. Lyngby Denmark http://www.bvg.dtu.dk 2001 DISCLAIMER Portions of this document may be illegible in electronic image products. Images are produced from the best available original document Report BYG DTU R-021 2001 ISSN 1601-2917 ISBN 87-7877-076-9 Executive summary This summary describes the results of a Ph.D. study that was carried out in the Energy Planning Group, Department for Civil Engineering, Technical University of Denmark, in a three-year period starting in August 1998 and ending in September 2001. The project was funded by a research grant from the Danish Energy Research Programme. The overall aim of this project is to investigate the linkages between energy use, life style and environmental impact. As a case of study, this report investigates the future possibilities for reducing the growth in greenhouse gas emissions from commercial civil air transport, that is passenger air travel and airfreight. The reason for this choice of focus is that we found that commercial civil air transport may become a relatively large energy consumer and greenhouse gas emitter in the future. For example, according to different scenarios presented by Intergovernmental Panel on Climate Change (IPCC), commercial civil air transport's fuel burn may grow by between 0,8 percent a factor of 1,6 and 16 between 1990 and 2050. The actual growth in fuel consumption will depend on the future growth in airborne passenger travel and freight and the improvement rate for the specific fuel efficiency. -
Conceptual Design for a Supersonic Advanced Military Trainer
Conceptual Design for a Supersonic Advanced Military Trainer A project presented to The Faculty of the Department of Aerospace Engineering San José State University In partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering by Royd A. Johansen May 2019 approved by Dr. Nikos Mourtos Faculty Advisor © 2019 Royd A. Johansen ALL RIGHTS RESERVED ABSTRACT CONCEPTUAL DESIGN FOR A SUPERSONIC ADVANCED MILITARY TRAINER by Royd A. Johansen The conceptual aircraft design project is based off the T-X program requirements for an advanced military trainer (AMT). The design process focused on a top-level design aspect, that followed the classic aircraft design process developed by J. Roskam’s Airplane Design. The design process covered: configuration selection, weight sizing, performance sizing, fuselage design, wing design, empennage design, landing-gear design, Class I weight and balance, static longitudinal and directional stability, subsonic drag polars, supersonic area rule applied to supersonic drag polars, V-n diagrams, Class II weight and balance, moments and products of inertia, and cost estimation. Throughout the process other materials and references are consulted to verify or develop a better understanding of the concepts in the Airplane Design series. ACKNOWLEDGEMENTS I would like to express my deep gratitude to Dr. Nikos Mourtos for his support throughout this project and his invaluable academic advisement throughout my undergraduate and graduate studies. I would also like to thank Professor Gonzalo Mendoza for introducing Aircraft Design to me as an undergraduate and for providing additional insights throughout my graduate studies. My thanks are also extended to Professor Jeanine Hunter for helping me develop my theoretical foundation in Dynamics, Flight Mechanics, and Aircraft Stability and Control. -
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.