Robert B. Elliott Is the Author of BUILD and FLY the FIRST FLYERS and Creator of the TOOTHPICK AIRFORCE™ Concept. Especially F
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The Aerodynamic Design of Wings with Cambered Span Having Minimum Induced Drag
https://ntrs.nasa.gov/search.jsp?R=19640006060 2020-03-24T06:40:56+00:00Z View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by NASA Technical Reports Server TR R-152 NASA- ..ZC_ L mm-4 -0-= I NATIONAL AERONAUTICS AND -----I- SPACE ADMINISTRATION LC)A~\c;i)p E AFW Wm* EP1 KIRTLANi =$= MS; TECHNICAL REPORT R-152 THE AERODYNAMIC DESIGN OF WINGS WITH CAMBERED SPAN HAVING MINIMUM INDUCED DRAG BY CLARENCE D. CONE, JR. 1963 ~ For -le by the Superintendent of Documents. US. Government Printing OIBce. Wasbingbn. D.C. 20402. Single copy price, 35 cents TECH LIBRARY KAFB, NM 00b8223 TECHNICAL REPORT R-152 THE AERODYNAMIC DESIGN OF WINGS WITH CAMBERED SPAN HAVING MINIMUM INDUCED DRAG By CLARENCE D. CONE, JR. Langley Research Center Langley Station, Hampton, Va. I CONTENTS Page SU~MMARY-________._...-.--..--.---------------------------------------- 1 INTRODUCTION __.._.._..__..___..~___.__._.._....~....~~-_--~~--~-------1 SYMBOLS___._____.___------.----------.---.--.---.---------------.--.--- 2 THE ])RAG POLAR OF CAMBERED-SPAN WINGS-_- - ...______________.__ 3 PROPERTIES OF CAMBERED WINGS HAVING MINIMUM INDUCED DRAG_._.._.___.~._.___~_._.___.._.____..__.__.-~~_-~---_---~~---------4 The Optimum Circulation IXstribution.. - -.- - -.- - - - - - - - - - - - - - - -.- - - - - - -.- - 4 The Effective Aspect Ratio ______________._._._____________________------5 THE DESIGN OF CAMBERED WINGS ____________________________________ 6 I>et,erininationof the Wing Shape for Maximum LID- - -.--_-___-___-___--__ 7 Specification of design requirements- - - - - - - - - - - - - - - -.-. - - - - - - - - - - - - - - - - 8 1)eterniination of minimum value of chord function- - - -.- - - - - - - - - - - - - - 8 Determination of wing profile-drag coefficient and optimum chord function- - 9 The optimum cruise altitude- -. -
10. Supersonic Aerodynamics
Grumman Tribody Concept featured on the 1978 company calendar. The basis for this idea will be explained below. 10. Supersonic Aerodynamics 10.1 Introduction There have actually only been a few truly supersonic airplanes. This means airplanes that can cruise supersonically. Before the F-22, classic “supersonic” fighters used brute force (afterburners) and had extremely limited duration. As an example, consider the two defined supersonic missions for the F-14A: F-14A Supersonic Missions CAP (Combat Air Patrol) • 150 miles subsonic cruise to station • Loiter • Accel, M = 0.7 to 1.35, then dash 25 nm - 4 1/2 minutes and 50 nm total • Then, must head home, or to a tanker! DLI (Deck Launch Intercept) • Energy climb to 35K ft, M = 1.5 (4 minutes) • 6 minutes at M = 1.5 (out 125-130 nm) • 2 minutes Combat (slows down fast) After 12 minutes, must head home or to a tanker. In this chapter we will explain the key supersonic aerodynamics issues facing the configuration aerodynamicist. We will start by reviewing the most significant airplanes that had substantial sustained supersonic capability. We will then examine the key physical underpinnings of supersonic gas dynamics and their implications for configuration design. Examples are presented showing applications of modern CFD and the application of MDO. We will see that developing a practical supersonic airplane is extremely demanding and requires careful integration of the various contributing technologies. Finally we discuss contemporary efforts to develop new supersonic airplanes. 10.2 Supersonic “Cruise” Airplanes The supersonic capability described above is typical of most of the so-called supersonic fighters, and obviously the supersonic performance is limited. -
N AL ADVISORY COMMITTEE for AERONAUTICS WASHINGTON July 12, 1957 NACA RM L57e24a
SOME FACTORS AFFECTING THE'STATIC LONGITU DIRECTIONAL STABILITY CHARACTEXISTICS OF SUPERSONIC AIRCRAFT CONFIGURATIONS By M. Leroy Spearman Langley Aeronautical Laboratory Langley Field, Va. N AL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON July 12, 1957 NACA RM L57E24a NATI SOME FACTORS AFFECTING TflE STATIC LONGITUDINAL AND DIRECTIONAL STABILITY CHARACTERISTICS OF SUPERSONIC AIRCRAFT CONFIGURATIO~S By M. kroy Spearman SUMMARY A survey is made of the problems introducei by Le ,,icreased -0ngi- tudinal stability and the reduced directional stability of aircraft operating in the low supersonic speed range. The longitudinal stability increases markedly at supersonic speeds and results in high drags due to trimming and in limited control for maneuvering. The large untrimmed pitching moments can be reduced and the control requirements alleviated to some extent through the use of fuselage camber. The use of canard configurations offers some promise of reducing the drag due to trimming and increasing the controllhbility. The directional stability generally deteriorates rapidly at super- sonic speeds because of the reduction in vertical-tail lift-curve slope coupled with the large unstable yawing moment of the fuselage. The vertical-tail contribution is shown to be affected by many factors including the wing position, the fuselage shape, and the horizontal-tail position. The directional stability can be increased, particularly at high angles of attack, by such devices as ventral fins and forebody strakes. In addition, indications are that the directional stability might be improved through modifications to the fuselage afterbody. INTRODUCTION Aircraft advancing from subsonic to low supersonic speeds frequently encounter performance and control problems as a result of significant changes in static stability characteristics. -
Further Devels'nent Ofthe Tunny
FURTHERDEVELS'NENT OF THETUNNY RIG E M H GIFFORDANO C PALNER Gi f ford and P art ners Carlton House Rlngwood Road Hoodl ands SouthamPton S04 2HT UK 360 1, lNTRODUCTION The idea of using a wing sail is not new, indeed the ancient junk rig is essentially a flat plate wing sail. The two essential characteristics are that the sail is stiffened so that ft does not flap in the wind and attached to the mast in an aerodynamically balanced way. These two features give several important advantages over so called 'soft sails' and have resulted in the junk rig being very successful on traditional craft. and modern short handed-cruising yachts. Unfortunately the standard junk rig is not every efficient in an aer odynamic sense, due to the presence of the mast beside the sai 1 and the flat shapewhich results from the numerousstiffening battens. The first of these problems can be overcomeby usi ng a double ski nned sail; effectively two junk sails, one on either side of the mast. This shields the mast from the airflow and improves efficiency, but it still leaves the problem of a flat sail. To obtain the maximumdrive from a sail it must be curved or cambered!, an effect which can produce over 5 more force than from a flat shape. Whilst the per'formanceadvantages of a cambered shape are obvious, the practical way of achieving it are far more elusive. One line of approach is to build the sail from ri gid componentswith articulated joints that allow the camberto be varied Ref 1!. -
Aerodynamic Study of a Two-Elements Wingsail for High Performance Multihull Yachts
Open Archive TOULOUSE Archive Ouverte ( OATAO ) OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. This is an author-deposited version published in: http://oatao.univ-toulouse.fr/ Eprints ID: 15683 To cite this version : Chapin, Vincent and Gourdain, Nicolas and Verdin, Nicolas and Fiumara, Alessandro and Senter, Julien Aerodynamic study of a two-elements wingsail for high performance multihull yachts. (2015) In: High Performance Yacht Design, 10 March 2015 - 12 March 2015 (Auckland, New Zealand). (Unpublished) Any correspondence concerning this service should be sent to the repository administrator: [email protected] 5th High Performance Yacht Design Conference Auckland, 10-12 March, 2015 AERODYNAMIC STUDY OF A TWO-ELEMENTS WINGSAIL FOR HIGH PERFORMANCE MULTIHULL YACHTS Vincent Chapin1, Nicolas Gourdain2, Nicolas Verdin3, Alessandro Fiumara4, Julien Senter5 Corresponding author : [email protected] Abstract. this paper is devoted to the numerical study of a 1:20th model-scale wingsail typical of America’s Cup yachts like AC72, AC62, AC45 or any C class catamaran to gain insight in its complex aerodynamic behavior and to prepare a wind-tunnel campain. This rigging has still not been much studied and needs more knowledge. This study is based on CFD simulations of the flow around the wingsail by resolving Navier-Stokes equations. Two modeling issues are investigated: the Unsteady Reynolds Average Navier-Stokes (URANS) and the Large Eddy Simulation (LES). These numerical approaches are used to characterize the wingsail aerodynamic behavior and variations with some key design and trim parameters (camber, slot width, angle of attack, flap thickness). -
On December 17, 1903, Orville and Wilbur Wright, Two Brothers From
On December 17, 1903, Orville and Wilbur Wright, two brothers from Dayton, Ohio, made the first sustained, controlled, powered flights from the sands of Kitty Hawk, North Carolina. Although 1899 we celebrate this date as the birth of aviation, the actual invention of the airplane was a painstaking and dangerous endeavor that started long before that day and continued long afterwards. To accomplish this task the Wrights built 7 aircraft, each a little better than the last, and tested them at two locations, Huffman 1900 Prairie (near Dayton) and Kitty Hawk. When they finally perfected a practical flying machine, they had made about approximately 2200 gliding flights and 158 powered flights. This work had occupied 2093 days in Dayton, 227 in Kitty 1901 Hawk, and about 20 days traveling between for a total of 2320 days over 6 years between 1899 and 1905! 1902 1903 1904 1905 Copyright © 2015 Bookworks, Inc. www.wright-brothers.org 1 “I am convinced that human flight is possible and practical.” Wilbur Wright to the Smithsonian Institution Aircraft tested: Model glider, 5-foot wingspan, flown as a kite. Longest flight: Unknown. Day 1 May 30, 1899 Wilbur’s letter to the Smithsonian. Bicycle maker Wilbur Wright tosses his hat into the scientific arena, writing to the Smithsonian Institution for information on mechanical flight and announcing his intention to “add my mite” to the emerging science of aeronautics. He is convinced that piloting an aircraft is a skill that can be learned, just like riding a bicycle. The problem, as he sees it, is control. Day 16 June 15, 1899* While twisting a small cardboard inner tube box, Wilbur discovers a simple method for changing the angle at which the wings of an aircraft meet the wind, enabling a pilot to roll into a turn. -
Wright 8 Rot Hers
WRIGHT 8 ROT HERS NATIONAL MEMORIAL They believed that a glider should be built in a way The brothers returned to Kill Devil Hills in 1902 with The brothers alternated in making three more flights that WRIGHT that the right and left wings could be presented at different a glider having a wingspan of 32 feet, built according to morning, each longer than the previous one; on the fourth angles to the wind for sidewise balance, and they deter their own figures on wind pressure. flight, Wilbur flew 852 feet in 59 seconds. mined to do this by warping or twisting the wings. To try It was soon evident that this 1902 glider showed a great As it seemed imprudent to fly at much height at first, it BROTHERS their scheme for control, they built a 5-foot model of a advance over any other ever built. In it, they made many was sometimes impossible to correct the up and down glider and, one day in 1899, tested it. Then they started glides of more than 600 feet against a 36-mile-an-hour motion of the machine before it struck the ground. This NATIONAL MEMORIAL thinking of a place for testing a man-carrying glider. After wind. No previous experimenter had ever dared try to accounts for the flights being so short. While the Wrights a study of wind records obtained from the Weather Bureau glide in so stiff a wind. and on-lookers were discussing the flights, a gust of wind at Washington, they picked Kitty Hawk. During their first With the 1902 glider the Wrights solved most of the struck the machine, turning it over and over, and damaging stay there in September 1900, they camped in a tent. -
Structural Design and Verification of an Innovative Whole Adaptive Variable Camber Wing
This is a repository copy of Structural design and verification of an innovative whole adaptive variable camber wing. White Rose Research Online URL for this paper: http://eprints.whiterose.ac.uk/155098/ Version: Accepted Version Article: Zhao, A, Zou, H, Jin, H et al. (1 more author) (2019) Structural design and verification of an innovative whole adaptive variable camber wing. Aerospace Science and Technology, 89. pp. 11-18. ISSN 1270-9638 https://doi.org/10.1016/j.ast.2019.02.032 © 2019 Published by Elsevier Masson SAS. This manuscript version is made available under the CC-BY-NC-ND 4.0 license http://creativecommons.org/licenses/by-nc-nd/4.0/. Reuse This article is distributed under the terms of the Creative Commons Attribution-NonCommercial-NoDerivs (CC BY-NC-ND) licence. This licence only allows you to download this work and share it with others as long as you credit the authors, but you can’t change the article in any way or use it commercially. More information and the full terms of the licence here: https://creativecommons.org/licenses/ Takedown If you consider content in White Rose Research Online to be in breach of UK law, please notify us by emailing [email protected] including the URL of the record and the reason for the withdrawal request. [email protected] https://eprints.whiterose.ac.uk/ 1 Structural design and verification of an innovative whole adaptive variable camber wing 2 Anmin Zhaoa,b, Hui Zoua, Haichuan Jina, Dongsheng Wena 3 aNational key Laboratory of Human Machine and Environment Engineering, Beihang 4 University, Beijing, 100191, China 5 bNational key laboratory of Computational Fluid Dynamics, Beihang University, Beijing, 6 100191, China 7 Abstract: A whole adaptive variable camber wing (AVCW) equipped with an innovative 8 double rib sheet (DRS) structure is experimentally and numerically studied in this work. -
The Wright Brothers' Drive for the Sky from Sand Dunes to Sonic Booms National Register of Historic Places FIRST WORD Reaffirmation
PRESERVING OUR NATION'S HERITAGE FALL 2003 Wings The Wright Brothers' Drive for the Sky From Sand Dunes to Sonic Booms National Register of Historic Places FIRST WORD Reaffirmation BY DE TEEL PATTERSON TILLER RECENTLY I MET WITH a small delegation from the Coalition of land tangible and accessible, IT REMAINS TO BE SEEN whether the Q/II Families—survivors and families and friends of those killed Coalition will be successful. New York City politics is a no-holds- in the attack on the World Trade Center on September 11, 2001. barred contact sport and much is at stake in the redevelopment of By their count their membership numbers around 3,000— the World Trade Center site. I hold out the hope that it may be roughly the same as lost that dark day more than two years ago. possible to find some compromise that preserves the remnants of The group's journey to Washington, DC, was borne of an inter the towers so that 100 or 1,000 years from now, Americans of est in seeing the remains of the towers designated as a National those generations will be able to walk over the bedrock and forge Historic Landmark. The putative leader of the delegation was a their own connections with this event that so changed our lives at young, purposeful man, Anthony Gardner, whose older brother, the beginning of the 21st century. Harvey Joseph Gardner, died in the collapse of the North Tower, THE MEETING WAS DIFFICULT and, at times, heart wrench ing. Everyone had a story making the tragedy compelling in mm We do what no book, television show, ways the media never could. -
Design of Canard Aircraft
APPENDIX C2: Design of Canard Aircraft This appendix is a part of the book General Aviation Aircraft Design: Applied Methods and Procedures by Snorri Gudmundsson, published by Elsevier, Inc. The book is available through various bookstores and online retailers, such as www.elsevier.com, www.amazon.com, and many others. The purpose of the appendices denoted by C1 through C5 is to provide additional information on the design of selected aircraft configurations, beyond what is possible in the main part of Chapter 4, Aircraft Conceptual Layout. Some of the information is intended for the novice engineer, but other is advanced and well beyond what is possible to present in undergraduate design classes. This way, the appendices can serve as a refresher material for the experienced aircraft designer, while introducing new material to the student. Additionally, many helpful design philosophies are presented in the text. Since this appendix is offered online rather than in the actual book, it is possible to revise it regularly and both add to the information and new types of aircraft. The following appendices are offered: C1 – Design of Conventional Aircraft C2 – Design of Canard Aircraft (this appendix) C3 – Design of Seaplanes C4 – Design of Sailplanes C5 – Design of Unusual Configurations Figure C2-1: A single engine, four-seat Velocity 173 SE just before touch-down. (Photo by Phil Rademacher) GUDMUNDSSON – GENERAL AVIATION AIRCRAFT DESIGN APPENDIX C2 – DESIGN OF CANARD AIRCRAFT 1 ©2013 Elsevier, Inc. This material may not be copied or distributed without permission from the Publisher. C2.1 Design of Canard Configurations It has already been stated that preference explains why some aircraft designers (and manufacturers) choose to develop a particular configuration. -
THE WRIGHT BROTHERS from Bicycles to Airplanes
THE WRIGHT BROTHERS from Bicycles to Airplanes Civil Air Patrol, the Official Auxiliary of the United States Air Force Where Imagination Takes Flight! A single copy of this publication may be ordered from: HQ CAP/ET MAXWELL AFB, AL 36112-6332 THE WRIGHT BROTHERS from Bicycles to Airplanes Edited by Judy Stone Layout and Graphics by Peggy Greenlee Published September 2002 by National Headquarters Civil Air Patrol Maxwell Air Force Base, Alabama i TABLE OF CONTENTS 1. Contents.............................................................................................................................................. ii 2. Acknowledgments............................................................................................................................... iv 3. Introduction......................................................................................................................................... 1 4. Teaching Tips...................................................................................................................................... 2 5. Student Record Sheet......................................................................................................................... 4 6. Wright Brothers Background Information............................................................................................ 5 7. Task #1 - Art + Teacher Lesson Plan.......................................................................................................... 13 + Student Information............................................................................................................ -
How Does the Camber of an Airfoil Affect the Lift-To-Drag-Ratio?
CALIFORNIA STATE SCIENCE FAIR 2006 PROJECT SUMMARY Name(s) Project Number Evan S. Stanford S0110 Project Title How Does the Camber of an Airfoil Affect the Lift-to-Drag-Ratio? Abstract Objectives/Goals The object of my science project was to determine how the camber of an airfoil affects its lift-to-drag ratio. Methods/Materials I tested the performance of several airfoils in a homemade wind tunnel. I carved four wings out of foam and coated them with paper, each with different cambers. I put each wing in the test section of my wind tunnel and then measured the lift and drag at various angles of attack. Results With this information, I was able to analyze the data in several ways. I found that all four of my cambered wings stalled at about +20 degrees and -20 degrees angle of attack. I found out how angle of attack affects lift, drag, and the lift-to-drag ratio. I also determined how camber affects lift-to-drag ratio and optimum angle of attack. I found that the airfoil with fifteen percent camber had the greatest efficiency. Conclusions/Discussion My hypothesis (0% would have the greatest efficiency) was not supported by my results. Instead, the airfoil with 15% camber had the greatest lift-to-drag ratio. In addition, I found that my data was consistent and logical. My results are useful for many applications; they can be used to build efficient wings for airplanes, ideal propellers, optimum spoilers for racecars, or effective fins for watercraft. Summary Statement My project used a homemade wind tunnel to test how the camber of an airfoil affects lift-to-drag ratio.