Design and Optimization of Aircraft Configuration for Minimum Drag
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
A Parametrical Transport Aircraft Fuselage Model for Preliminary Sizing and Beyond
Deutscher Luft- und Raumfahrtkongress 2014 DocumentID: 340104 A PARAMETRICAL TRANSPORT AIRCRAFT FUSELAGE MODEL FOR PRELIMINARY SIZING AND BEYOND D. B. Schwinn, D. Kohlgrüber, J. Scherer, M. H. Siemann German Aerospace Center (DLR), Institute of Structures and Design (BT), Pfaffenwaldring 38-40, 70569 Stuttgart, Germany [email protected], tel.: +49 (0) 711 6862-221, fax: +49 (0) 711 6862-227 Abstract Aircraft design generally comprises three consecutive phases: Conceptual, preliminary and detailed design phase. The preliminary design phase is of particular interest as the basic layout of the primary structure is defined. Up to date, semi-analytical methods are widely used in this design stage to estimate the structural mass. Although these methods lead to adequate results for the major aircraft components of standard configurations, the evaluation of new configurations (e.g. box wing, blended wing body) or specific structural components with complex loading conditions (e.g. center wing box) is very challenging and demands higher fidelity approaches based on Finite Elements (FE). To accelerate FE model generation in multi-disciplinary design approaches, automated processes have been introduced. In order to easily couple different tools, a standardized data format – CPACS (Common Parameterized Aircraft Configuration Schema) - is used. The versatile structural description in CPACS, the implementation in model generation tools but also current limitations and future enhancements will be discussed. Recent development in the progress of numerical process chains for structural sizing but also for further applications including crash on solid ground and ditching (emergency landing on water) are presented in this paper. flight and ground load cases, e.g. +2.5g maneuver, gust 1. -
Flying Wing Concept for Medium Size Airplane
ICAS 2002 CONGRESS FLYING WING CONCEPT FOR MEDIUM SIZE AIRPLANE Tjoetjoek Eko Pambagjo*, Kazuhiro Nakahashi†, Kisa Matsushima‡ Department of Aeronautics and Space Engineering Tohoku University, Japan Keywords: blended-wing-body, inverse design Abstract The flying wing is regarded as an alternate This paper describes a study on an alternate configuration to reduce drag and structural configuration for medium size airplane. weight. Since flying wing possesses no fuselage Blended-Wing-Body concept, which basically is it may have smaller wetted area than the a flying wing configuration, is applied to conventional airplane. In the conventional airplane for up to 224 passengers. airplane the primary function of the wing is to An aerodynamic design tools system is produce the lift force. In the flying wing proposed to realize such configuration. The configuration the wing has to carry the payload design tools comprise of Takanashi’s inverse and provides the necessary stability and control method, constrained target pressure as well as produce the lift. The fuselage has to specification method and RAPID method. The create lift without much penalty on the drag. At study shows that the combination of those three the same time the fuselage has to keep the cabin design methods works well. size comfortable for passengers. In the past years several flying wings have been designed and flown successfully. The 1 Introduction Horten, Northrop bombers and AVRO are The trend of airplane concept changes among of those examples. However the from time to time. Speed, size and range are application of the flying wing concepts were so among of the design parameters. -
CANARD.WING LIFT INTERFERENCE RELATED to MANEUVERING AIRCRAFT at SUBSONIC SPEEDS by Blair B
https://ntrs.nasa.gov/search.jsp?R=19740003706 2020-03-23T12:22:11+00:00Z NASA TECHNICAL NASA TM X-2897 MEMORANDUM CO CN| I X CANARD.WING LIFT INTERFERENCE RELATED TO MANEUVERING AIRCRAFT AT SUBSONIC SPEEDS by Blair B. Gloss and Linwood W. McKmney Langley Research Center Hampton, Va. 23665 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • DECEMBER 1973 1.. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TM X-2897 4. Title and Subtitle 5. Report Date CANARD-WING LIFT INTERFERENCE RELATED TO December 1973 MANEUVERING AIRCRAFT AT SUBSONIC SPEEDS 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. L-9096 Blair B. Gloss and Linwood W. McKinney 10. Work Unit No. 9. Performing Organization Name and Address • 760-67-01-01 NASA Langley Research Center 11. Contract or Grant No. Hampton, Va. 23665 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Memorandum National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington , D . C . 20546 15. Supplementary Notes 16. Abstract An investigation was conducted at Mach numbers of 0.7 and 0.9 to determine the lift interference effect of canard location on wing planforms typical of maneuvering fighter con- figurations. The canard had an exposed area of 16.0 percent of the wing reference area and was located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. In addition, the canard could be located at two longitudinal stations. -
Systems Engineering Approach in Aircraft Design Education; Techniques and Challenges
Paper ID #11232 Systems Engineering Approach in Aircraft Design Education; Techniques and Challenges Prof. Mohammad Sadraey, Daniel Webster College Mohammad H. Sadraey is an Associate Professor in the Engineering School at the Daniel Webster Col- lege, Nashua, New Hampshire, USA. Dr. Sadraey’s main research interests are in aircraft design tech- niques, and design and automatic control of unmanned aircraft. He received his MSc. in Aerospace Engineering in 1995 from RMIT, Melbourne, Australia, and his Ph.D. in Aerospace Engineering from the University of Kansas, Kansas, USA. Dr. Sadraey is a senior member of the American Institute of Aeronautics and Astronautics (AIAA), and a member of American Society for Engineering Education (ASEE). Prof. Nicholas Bertozzi, Daniel Webster College Nick Bertozzi is a Professor of Engineering at Daniel Webster College (DWC) and Dean of the School of Engineering and Computer Science (SECS). His major interest over the past 18 years has been the concurrent engineering design process, an interest that was fanned into flame by attending an NSF faculty development workshop in 1996 led by Ron Barr and Davor Juricic. Nick has a particular interest in help- ing engineering students develop good communications skills and has made this a SECS priority. Over the past ten years he and other engineering and humanities faculty colleagues have mentored a number of undergraduate student teams who have co-authored and presented papers and posters at Engineering Design Graphics Division (EDGD) and other ASEE, CDIO (www.cdio.org), and American Institute of Aeronautics and Astronautics (AIAA) meetings as well. Nick was delighted to serve as the EDGD pro- gram chair for the 2008 ASEE Summer Conference and as program co-chair with Kathy Holliday-Darr for the 68th EDGD Midyear meeting at WPI in October 2013. -
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. -
Aircraft Requirements for Sustainable Regional Aviation
aerospace Article Aircraft Requirements for Sustainable Regional Aviation Dominik Eisenhut 1,*,† , Nicolas Moebs 1,† , Evert Windels 2, Dominique Bergmann 1, Ingmar Geiß 1, Ricardo Reis 3 and Andreas Strohmayer 1 1 Institute of Aircraft Design, University of Stuttgart, 70569 Stuttgart, Germany; [email protected] (N.M.); [email protected] (D.B.); [email protected] (I.G.); [email protected] (A.S.) 2 Aircraft Development and Systems Engineering (ADSE) BV, 2132 LR Hoofddorp, The Netherlands; [email protected] 3 Embraer Research and Technology Europe—Airholding S.A., 2615–315 Alverca do Ribatejo, Portugal; [email protected] * Correspondence: [email protected] † These authors contributed equally to this work. Abstract: Recently, the new Green Deal policy initiative was presented by the European Union. The EU aims to achieve a sustainable future and be the first climate-neutral continent by 2050. It targets all of the continent’s industries, meaning aviation must contribute to these changes as well. By employing a systems engineering approach, this high-level task can be split into different levels to get from the vision to the relevant system or product itself. Part of this iterative process involves the aircraft requirements, which make the goals more achievable on the system level and allow validation of whether the designed systems fulfill these requirements. Within this work, the top-level aircraft requirements (TLARs) for a hybrid-electric regional aircraft for up to 50 passengers are presented. Apart from performance requirements, other requirements, like environmental ones, Citation: Eisenhut, D.; Moebs, N.; are also included. -
Aircraft Design Final Design Review
Group 7 AIRCRAFT DESIGN FINAL DESIGN REVIEW March 20, 2013 Sagun Bajracharya Roger Francis Tim Tianhang Teng Guang Wei Yu Abstract This document summarizes the work that group 7 has done insofar regarding the design of a radio-controlled plane with respect to the requirements that were put forward by the course (AER406, 2013). This report follows the same format as the presentation where we inform the reader where the current design is, how the group progressed towards that design and how we started. This report also summarizes a number of the important parameters required for a conceptual design like the cargo type & amount,Wing aspect ratio, Optimum Airfoil lift(CL), Thrust to weight ratio & Takeoff distance. In addition, this report presents the plane's wing and tail design, stability analysis and a mass breakdown. The report finally ends with pictures of the current design. 2 Contents 1 Design Overview6 2 Required Parameters6 3 Trade Studies6 3.1 Wing Design....................................... 7 3.2 Wing Configuration................................... 8 3.3 Fuselage Design..................................... 8 3.4 Tail Design ....................................... 9 3.5 Overall Selection .................................... 10 3.6 Parameters from Reference Designs.......................... 11 4 Flight Score Optimization 11 4.1 Cargo Selection..................................... 11 4.2 Propeller Selection ................................... 12 4.3 Flight Parameter Selection............................... 13 5 Wing Design 16 5.1 -
General Aviation Aircraft Design
Contents 1. The Aircraft Design Process 3.2 Constraint Analysis 57 3.2.1 General Methodology 58 1.1 Introduction 2 3.2.2 Introduction of Stall Speed Limits into 1.1.1 The Content of this Chapter 5 the Constraint Diagram 65 1.1.2 Important Elements of a New Aircraft 3.3 Introduction to Trade Studies 66 Design 5 3.3.1 Step-by-step: Stall Speed e Cruise Speed 1.2 General Process of Aircraft Design 11 Carpet Plot 67 1.2.1 Common Description of the Design Process 11 3.3.2 Design of Experiments 69 1.2.2 Important Regulatory Concepts 13 3.3.3 Cost Functions 72 1.3 Aircraft Design Algorithm 15 Exercises 74 1.3.1 Conceptual Design Algorithm for a GA Variables 75 Aircraft 16 1.3.2 Implementation of the Conceptual 4. Aircraft Conceptual Layout Design Algorithm 16 1.4 Elements of Project Engineering 19 4.1 Introduction 77 1.4.1 Gantt Diagrams 19 4.1.1 The Content of this Chapter 78 1.4.2 Fishbone Diagram for Preliminary 4.1.2 Requirements, Mission, and Applicable Regulations 78 Airplane Design 19 4.1.3 Past and Present Directions in Aircraft Design 79 1.4.3 Managing Compliance with Project 4.1.4 Aircraft Component Recognition 79 Requirements 21 4.2 The Fundamentals of the Configuration Layout 82 1.4.4 Project Plan and Task Management 21 4.2.1 Vertical Wing Location 82 1.4.5 Quality Function Deployment and a House 4.2.2 Wing Configuration 86 of Quality 21 4.2.3 Wing Dihedral 86 1.5 Presenting the Design Project 27 4.2.4 Wing Structural Configuration 87 Variables 32 4.2.5 Cabin Configurations 88 References 32 4.2.6 Propeller Configuration 89 4.2.7 Engine Placement 89 2. -
The Changing Structure of the Global Large Civil Aircraft Industry and Market: Implications for the Competitiveness of the U.S
ABSTRACT On September 23, 1997, at the request of the House Committee on Ways and Means (Committee),1 the United States International Trade Commission (Commission) instituted investigation No. 332-384, The Changing Structure of the Global Large Civil Aircraft Industry and Market: Implications for the Competitiveness of the U.S. Industry, under section 332(g) of the Tariff Act of 1930, for the purpose of exploring recent developments in the global large civil aircraft (LCA) industry and market. As requested by the Committee, the Commission’s report on the investigation is similar in scope to the report submitted to the Senate Committee on Finance by the Commission in August 1993, initiated under section 332(g) of the Tariff Act of 1930 (USITC inv. No. 332-332, Global Competitiveness of U.S. Advanced-Technology Manufacturing Industries: Large Civil Aircraft, Publication 2667) and includes the following information: C A description of changes in the structure of the global LCA industry, including the Boeing-McDonnell Douglas merger, the restructuring of Airbus Industrie, the emergence of Russian producers, and the possibility of Asian parts suppliers forming consortia to manufacture complete airframes; C A description of developments in the global market for aircraft, including the emergence of regional jet aircraft and proposed jumbo jets, and issues involving Open Skies and free flight; C A description of the implementation and status of the 1992 U.S.-EU Large Civil Aircraft Agreement; C A description of other significant developments that affect the competitiveness of the U.S. LCA industry; and C An analysis of the aforementioned structural changes in the LCA industry and market to assess the impact of these changes on the competitiveness of the U.S. -
Improving the Aircraft Design Process Using Web-Based Modeling and Simulation
Reed. J.;I.. Fdiet7, G. .j. unci AJjeh. ‘-1. ,-I Improving the Aircraft Design Process Using Web-based Modeling and Simulation John A. Reed?, Gregory J. Follenz, and Abdollah A. Afjeht tThe University of Toledo 2801 West Bancroft Street Toledo, Ohio 43606 :NASA John H. Glenn Research Center 2 1000 Brookpark Road Cleveland, Ohio 44135 Keywords: Web-based simulation, aircraft design, distributed simulation, JavaTM,object-oriented ~~ ~ ~ ~~ Supported by the High Performance Computing and Communication Project (HPCCP) at the NASA Glenn Research Center. Page 1 of35 Abstract Designing and developing new aircraft systems is time-consuming and expensive. Computational simulation is a promising means for reducing design cycle times, but requires a flexible software environment capable of integrating advanced multidisciplinary and muitifidelity analysis methods, dynamically managing data across heterogeneous computing platforms, and distributing computationally complex tasks. Web-based simulation, with its emphasis on collaborative composition of simulation models, distributed heterogeneous execution, and dynamic multimedia documentation, has the potential to meet these requirements. This paper outlines the current aircraft design process, highlighting its problems and complexities, and presents our vision of an aircraft design process using Web-based modeling and simulation. Page 2 of 35 1 Introduction Intensive competition in the commercial aviation industry is placing increasing pressure on aircraft manufacturers to reduce the time, cost and risk of product development. To compete effectively in today’s global marketplace, innovative approaches to reducing aircraft design-cycle times are needed. Computational simulation, such as computational fluid dynamics (CFD) and finite element analysis (FEA), has the potential to compress design-cycle times due to the flexibility it provides for rapid and relatively inexpensive evaluation of alternative designs and because it can be used to integrate multidisciplinary analysis earlier in the design process [ 171. -
Overall Design and Assessment of Aircraft Concepts with Boundary Layer Ingesting Engines
OVERALL DESIGN AND ASSESSMENT OF AIRCRAFT CONCEPTS WITH BOUNDARY LAYER INGESTING ENGINES D. Silberhorn German Aerospace Center (DLR), Institute of System Architectures in Aeronautics, 21129 Hamburg, Germany C. Hollmann, M. Mennicken, F. Wolters German Aerospace Center (DLR), Institute of Propulsion Technology, 51147 Cologne, Germany F. Eichner German Aerospace Center (DLR), Institute of Aeroelasticity, 37073 Göttingen, Germany M. Staggat German Aerospace Center (DLR), Institute of Propulsion Technology, 10623 Berlin, Germany Abstract The assessment of a kerosene driven aircraft concept with a boundary layer ingesting propulsion (BLI) system is content of this paper. The objective is to determine the potential of this BLI technology for short/medium range single aisle aircraft. For this an overall aircraft design (OAD) interpretation of a current Airbus A320neo, called D165, is chosen to be the reference to calibrate the design and assessment methodology. However, the final technology integration results are compared to the Baseline D165-2035 assuming technology level maturation for 2035. This D165-2035 aircraft is equipped with two geared turbofan engines with an increased bypass-ratio of 15.3 at take-off condition. To evaluate the various phenomena driving the aircraft performance and to isolate the impact of the integration of the BLI propulsion system, two intermediate aircraft with rear-mounted engines have been designed. The first one features structurally and flight performance driven positioned rear engines at the location of the rear pressure bulkhead and the second one takes additional constraints into account considering the possibility of burying the engines into the fuselage at the next step without any interaction with the passenger cabin and hence the bulkhead. -
Aircraft Design Projects
Aircraft Design Projects “fm” — 2003/3/11 — pagei—#1 Dedications To Jessica, Maria, Edward, Robert and Jonothan – in their hands rests the future. To my father, J. F. Marchman, Jr, for passing on to me his love of airplanes and to my teacher, Dr Jim Williams, whose example inspired me to pursue a career in education. “fm” — 2003/3/11 — page ii — #2 Aircraft Design Projects for engineering students Lloyd R. Jenkinson James F. Marchman III OXFORD AMSTERDAM BOSTON LONDON NEW YORK PARIS SAN DIEGO SAN FRANCISCO SINGAPORE SYDNEY TOKYO “fm” — 2003/3/11 — page iii — #3 Butterworth-Heinemann An imprint of Elsevier Science Linacre House, Jordan Hill, Oxford OX2 8DP 200 Wheeler Road, Burlington MA 01803 First published 2003 Copyright © 2003, Elsevier Science Ltd. All rights reserved No part of this publication may be reproduced in any material form (including photocopying or storing in any medium by electronic means and whether or not transiently or incidentally to some other use of this publication) without the written permission of the copyright holder except in accordance with the provisions of the Copyright, Designs and Patents Act 1988 or under the terms of a licence issued by the Copyright Licensing Agency Ltd, 90 Tottenham Court Road, London, England W1T 4LP. Applications for the copyright holder’s written permission to reproduce any part of this publication should be addressed to the publisher Permissions may be sought directly from Elsevier’s Science and Technology Rights Department in Oxford, UK: phone: (+44) (0) 1865 843830; fax: (+44) (0) 1865 853333; e-mail: [email protected].